A multi-wing folding wing deployment uniformity testing device

Abstract

The present application relates to a kind of multi-wing folding wing deployment consistency test device, belong to detection equipment field, solve the measurement precision of existing folding wing deployment time detection equipment is lower, cannot accurately measure the problem of folding wing deployment time and synchronism.The present application includes: folding wing fixed component and wing bundle release component;Wing bundle release component includes: folding wing fixed pressing plate, in-place photoelectric sensor and folding wing fixed base plate;The folding wing mechanism to be detected is clamped and fixed between folding wing fixed base plate and folding wing fixed pressing plate;In-place photoelectric sensor monitors whether the wing of folding wing mechanism is deployed in place;Wing bundle release component includes: bundle release base, wing bundle release base plate, electric push rod and locking assembly;Locking assembly is arranged on wing bundle release base plate and locks or unlocks the wing of folding wing mechanism;Electric push rod is used to drive wing bundle release base plate displacement.The present application realizes the detection of the deployment synchronism of multiple wings of folding wing.

Description

Technical Field

[0001] This invention relates to the field of testing equipment technology, and in particular to a testing device for the consistency of multi-bladed folding wing deployment. 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 multi-bladed folding wing deployment consistency testing equipment is expensive, has complex data processing, and low measurement accuracy, making it unable to accurately measure the folding wing deployment time and synchronization.

[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 multi-bladed folding wing deployment consistency testing device to solve the problem that existing folding wing deployment time detection devices have low measurement accuracy and cannot accurately measure the folding wing deployment time and synchronization.

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

[0007] A multi-blade folding wing deployment consistency testing device includes: a folding wing fixing assembly and a blade assembly; the blade assembly includes: a folding wing fixing plate, a positioning photoelectric sensor and a folding wing fixing base plate; the folding wing mechanism to be tested is clamped and fixed between the folding wing fixing base plate and the folding wing fixing plate; the positioning photoelectric sensor is used to monitor whether the blades of the folding wing mechanism are deployed in place;

[0008] 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.

[0009] Furthermore, when the folding wing mechanism is in the folded state, the wing bends downward and is limited by the locking assembly; when the wing bundle substrate moves downward, the locking assembly separates from the wing and releases the limitation on the wing.

[0010] Furthermore, the folding wing fixing assembly also includes: a sensor fixing bracket; multiple sensor fixing brackets are circumferentially arranged on the folding wing fixing base plate; and the positioning photoelectric sensor is fixedly installed on the sensor fixing bracket.

[0011] Furthermore, a screw is vertically arranged on the folding wing fixing base plate; a through hole is provided on the folding wing fixing pressure plate; the folding wing fixing pressure plate is sleeved on the screw through the through hole, and a wing nut is installed on the part of the screw protruding from the folding wing fixing pressure plate.

[0012] Furthermore, the positioning photoelectric sensor has a C-shaped structure with a concave groove.

[0013] Specifically, the housing of the positioning photoelectric sensor has a C-shaped structure, and the photoelectric probe of the positioning photoelectric sensor is set at the end face of the groove; the protrusions extending from the housing on both sides block the photoelectric probe on the inner side, ensuring the detection accuracy of the positioning photoelectric sensor.

[0014] Furthermore, when the wing is deployed into position, it can be engaged in the groove of the positioning photoelectric sensor.

[0015] Furthermore, the vane beam amplification substrate is slidably mounted on the beam amplification base via a linear bearing and a guide slide.

[0016] Furthermore, the linear bearing is fixedly mounted on the beam-forming base, and the guide slide is fixedly mounted on the wing beam-forming substrate; the guide slide is sleeved inside the linear bearing and can slide relative to it.

[0017] Furthermore, the vane beaming substrate has an annular structure; multiple sets of locking components are provided and are circumferentially mounted on the vane beaming substrate.

[0018] Furthermore, 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.

[0019] Specifically, the folding wing mechanism includes a main structure and a wing piece; the wing piece is 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, and the wing piece bends downward and is limited by the locking pin.

[0020] In this invention, when the locking post limits the wing, that is, when the locking post is in the locked state, the locking post protrudes from the wing bundle substrate and can prevent the wing from unfolding.

[0021] Specifically, the side of the guide shaft seat is provided with a T-shaped limiting groove; a handle screw is fixedly installed on the guide shaft, the handle screw is set perpendicular to the guide shaft and extends out from the T-shaped limiting groove.

[0022] Specifically, the T-shaped limiting groove includes a transverse groove and a longitudinal groove that are interconnected.

[0023] Specifically, when the handle screw slides in the longitudinal groove, it can drive the guide shaft and locking pin to move up and down, thereby causing the locking pin to switch between locked and unlocked states.

[0024] When the handle screw is located at the highest point of the longitudinal groove or in the transverse groove, the locking pin is in a locked state; when the locking pin is located at the lowest point of the longitudinal groove, the locking pin is in an unlocked state. When the locking pin is in the locked state, the wing cannot rotate freely; when the locking pin is in the unlocked state, the wing can rotate freely.

[0025] The technical solution of this invention can achieve at least one of the following effects:

[0026] 1. The multi-blade folding wing deployment consistency testing device of the present invention limits or releases the blades of the folding wing through the blade bundling assembly, so that the blades can maintain the folded state or switch from the folded state to the deployed state; when the blades are deployed, the positioning photoelectric sensor on the folding wing fixing assembly monitors the positioning time of each blade, thereby enabling the monitoring of the deployment consistency of multiple blades of the folding wing.

[0027] 2. In the multi-bladed folding wing deployment consistency testing device of the present invention, the positioning photoelectric sensor is a C-shaped structure with a concave groove. The present invention achieves the blocking of the positioning photoelectric sensor by having the wing blades inserted into the groove, thereby enabling the monitoring of the wing blade deployment moment. The C-shaped positioning photoelectric sensor used in the present invention ensures the accuracy of the detection results.

[0028] 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

[0029] 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.

[0030] Figure 1 This is a schematic diagram of the usage state of the multi-bladed folding wing deployment consistency testing device of Embodiment 1 of the present invention;

[0031] Figure 2 This is the multi-bladed folding wing deployment consistency testing device of Embodiment 1 of the present invention;

[0032] Figure 3 This refers to the folding wing fixing component of the multi-blade folding wing deployment consistency testing device of Embodiment 1 of the present invention;

[0033] Figure 4 This is the support column of the multi-bladed folding wing deployment consistency testing device of Embodiment 1 of the present invention;

[0034] Figure 5 This is the locked state of the winglet bundle assembly of the multi-winglet folding wing deployment consistency testing device of the present invention.

[0035] Figure 6 This is the unlocked state of the winglet bundle assembly of the multi-winglet folding wing deployment consistency testing device of the present invention.

[0036] Figure 7 for Figure 5 , Figure 6 The locking state of the locking assembly of the vane bundle assembly;

[0037] Figure 8 for Figure 7 The unlocking status of the locking component;

[0038] Figure 9 For server racks.

[0039] Figure label:

[0040] 1- Folding wing fixing assembly; 2- Support column; 3- Wing blade assembly; 4- Cabinet;

[0041] 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;

[0042] 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;

[0043] 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;

[0044] 3071 - Guide shaft seat; 3072 - T-shaped limiting groove; 3073 - Guide shaft; 3074 - Locking pin; 3075 - Handle screw; 3076 - Fixing screw; 3077 - Return spring;

[0045] 401 - Upper mounting plate; 402 - Tester mounting hole; 403 - Casters. Detailed Implementation

[0046] 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.

[0047] A specific embodiment of the present invention discloses a multi-blade folding wing deployment consistency testing device, comprising two parts: a folding wing fixing assembly 1 and a blade bundling assembly 3.

[0048] Folding wing fixing component 1, such as Figure 3 As shown; Folding winglet assembly 3 Figure 5 , Figure 6 As shown, it is mainly used to realize functions such as installation and fixation of folding wings, wing locking, synchronous release of winglets, and measurement of winglet deployment time.

[0049] like Figure 3 As shown, the folding wing fixing assembly 1 includes: a folding wing fixing plate 101, a positioning photoelectric sensor 102, and a folding wing fixing base plate 104; the folding wing mechanism to be detected is clamped and fixed between the folding wing fixing base plate 104 and the folding wing fixing plate 101; the positioning photoelectric sensor 102 is used to monitor whether the wing flaps of the folding wing mechanism are unfolded into position.

[0050] 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.

[0051] When the folding wing mechanism is in the folded state, the wing bends downward and is limited by the locking assembly 307; when the wing bundle substrate 302 moves downward, the locking assembly 307 separates from the wing and releases the limitation on the wing.

[0052] In practice, the monitoring device of this invention is used to detect the deployment time of the folding wing: First, the folding wing to be tested is installed and fixed on the folding wing fixing assembly 1, and the winglets are locked and limited by the winglet bundling assembly 3; the folding wing is unlocked during detection; the winglets of the folding wing are deployed, and the arrival time of each winglet is monitored by the positioning photoelectric sensor 102; the positioning photoelectric sensor 102 is at a low level when it is blocked by a winglet, and at a high level when it is not blocked by a winglet; 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 arrival signal.

[0053] Furthermore, since the winglets of the folding wing have a certain length, the spacing between the folding wing fixing assembly 1 and the winglet bundling assembly 3 is set according to the length of the folding wing winglets to be tested.

[0054] The methods for fixing the positional relationship between the folding wing fixing assembly 1 and the winglet bundling assembly 3 of the present invention include, but are not limited to, the following two:

[0055] (I) First type:

[0056] In one embodiment of the present invention, the folding wing fixing assembly 1 and the winglet bundling assembly 3 are stacked vertically, and the folding wing fixing assembly 1 and the winglet bundling assembly 3 are connected by a support column 2, such as... Figure 2 As shown. Further, an unlocking photoelectric sensor 206 is installed on the outer wall of the support column 2 or on the winglet assembly 3.

[0057] like Figure 4 The image shows the unlocking photoelectric sensor 206 installed on the support column 2. Further, a mounting hole 202 for fixing the folding wing mounting base 104 is provided on the top of the support column 2; a reset switch 203, a power switch 204, an unlocking photoelectric mounting base 205, an unlocking photoelectric sensor 206, and a side cover 207 are provided on the side of the support column 2. 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.

[0058] 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.

[0059] like Figure 1 , Figure 9As shown, a cabinet 4 is disposed below the winglet bundle assembly 3; the bundle 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 winglet bundle assembly 3. The interior of the cabinet 4 is used to house the electrical components required to implement the testing method of this invention.

[0060] Specifically, the support column 2 is a cylindrical structure with a central cavity, and the central cavity is connected to the internal space of the cabinet 4, which facilitates the arrangement of cables.

[0061] Furthermore, casters 403 are provided at the bottom of the cabinet 4 to facilitate the transfer of the testing device of the present invention.

[0062] (II) The second type:

[0063] In another embodiment of the present invention, the folding wing fixing assembly 1 and the winglet bundle assembly 3 are arranged horizontally in the left and right directions, and their axes coincide. The folding wing fixing assembly 1 and the winglet bundle assembly 3 are supported by a first support frame and a second support frame, respectively; both the first support frame and the second support frame are steel frame structures. The first support frame is welded and fixed to the folding wing fixing base plate 104, and the second support frame is welded and fixed to the bundle base 301. The distance between the folding wing fixing assembly 1 and the winglet bundle assembly 3 can be adjusted by adjusting the distance between the first support frame and the second support frame; thereby enabling the testing device of the present invention to adapt to folding wing mechanisms of different sizes and types.

[0064] Specifically, the present invention does not limit the structural shape of the support frame, as long as it can achieve the function of supporting and fixing the folding wing fixing component 1 and the winglet bundle assembly 3, and the first support frame and the second support frame avoid the movement trajectory of the winglet.

[0065] Furthermore, an unlocking photoelectric sensor 206 (not shown in the figure) is integrated and installed on the side of the locking post 3074 of the multiple locking components 307 of the winglet assembly 3. When the locking post 3074 locks the winglet, the winglet blocks the unlocking photoelectric sensor 206 on the locking post 3074. When the locking post 3074 releases the winglet, the unlocking photoelectric sensor is not blocked.

[0066] After fixing the positions of the folding wing fixing assembly 1 and the winglet deployment assembly 3 using the two methods described above: before the winglets unlock, the winglets block the unlocking photoelectric sensor 206, resulting in a low level for the unlocking photoelectric sensor 206 and a high level for the positioning photoelectric sensor 102; after the winglets are deployed, the winglets block the positioning photoelectric sensor, resulting in a high level for the unlocking photoelectric sensor 206 and a low level for the positioning photoelectric sensor 102. This invention records the release and deployment times of multiple winglets by monitoring the level changes of the unlocking photoelectric sensor 206 and the positioning photoelectric sensor 102, thereby detecting the deployment time and asynchronous deployment time of the winglets.

[0067] During implementation: The unlocking time of each winglet is recorded by the level change of the release photoelectric sensor; when the release photoelectric sensor detects the first unlocking signal, the timer is started.

[0068] Based on the measured unlocking and arrival times of each winglet, the deployment time Ti of each winglet, the unlocking time difference Ts of multiple winglets, and the arrival time difference Te can be calculated.

[0069] Furthermore, when using the support column 2 to fix the folding wing fixing assembly 1, a display window panel 201 is installed on the surface of the support column 2; such as Figure 2 , Figure 4 As shown. When the folding wing fixing assembly 1 and the winglet bundle assembly 3 are fixed using a support frame, the display window 201 is mounted on the first support frame or the second support frame (not shown in the figure). The display window 201 includes multiple digital tubes for displaying the time signals detected by the unlocking photoelectric sensor and the positioning photoelectric sensor.

[0070] Specifically, the deployment time Ti, wing unlocking asynchronous time Ts, and wing deployment asynchronous time Te of each wing are displayed via multiple digital tubes on the display window panel 201. The wing deployment time Ti is the difference between the wing's arrival time and unlocking time; where i is the number of the multiple winglets; i is a natural number greater than or equal to 1; the maximum value of i is determined based on the number of winglets in the folding wing. The wing unlocking asynchronous time Ts is the difference between the acquisition time of the last winglet unlocking signal and the acquisition time of the first winglet unlocking signal. The wing 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 reaches the corresponding positioning photoelectric sensor.

[0071] The following describes the folding wing fixing components:

[0072] The main function of the wing fixing assembly 1 is to install and fix the folding wing mechanism to be tested, and it is equipped with four positioning photoelectric sensors 102 to detect whether the four wings have been deployed in place at all times, and send the acquired positioning signals to the control module to calculate the deployment time.

[0073] In one specific embodiment of the present invention, the folding wing fixing assembly 1 further includes: a sensor fixing bracket 103; a plurality of sensor fixing brackets 103 are circumferentially arranged on the folding wing fixing base plate 104; and the positioning photoelectric sensor 102 is fixedly installed on the sensor fixing bracket 103.

[0074] Furthermore, a screw is vertically arranged on the folding wing fixing base plate 104; a through hole is provided on the folding wing fixing pressure plate 101; the folding wing fixing pressure plate 101 is sleeved on the screw through the through hole, and a wing nut 105 is installed on the part of the screw protruding from the folding wing fixing pressure plate 101.

[0075] 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.

[0076] 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.

[0077] 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.

[0078] 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.

[0079] When securing the folding wings:

[0080] 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.

[0081] The following describes the winglet bundle assembly:

[0082] In one specific embodiment of the present invention, the vane beam amplification substrate 302 is slidably mounted on the beam amplification base 301 via a linear bearing 303 and a guide slide rod 304. The vane beam amplification substrate 302 and the beam amplification base 301 are arranged parallel to each other.

[0083] Specifically, such as 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 assembly substrate 302. The linear bearings 303 are fixedly mounted on the beam assembly base 301, and the guide slides 304 are fixedly mounted on the vane beam assembly substrate 302; the guide slides 304 are sleeved inside the linear bearings 303 and can slide relative to them.

[0084] When the winglet beaming substrate 302 is displaced relative to the beaming base 301, the locking assembly 307 is displaced relative to the winglet as a whole, thereby locking or unlocking the winglet.

[0085] The present invention ensures the stability of the relative displacement between the winglet beam-forming substrate 302 and the beam-forming base 301 by setting four sets of linear bearings 303 and guide slide rods 304. This ensures that the winglet beam-forming substrate 302 only translates relative to the beam-forming base 301 and does not deflect, thereby ensuring the synchronous unlocking of the winglets by the four sets of locking components 307 and ensuring the accuracy of the detection results.

[0086] like 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.

[0087] Furthermore, the installation method of the electric linear actuator 305 is as follows:

[0088] like Figure 5 , Figure 6As shown, the motion connecting rod 310 is fixedly mounted on the winglet beam amplification base plate 302, and the push rod base 306 is fixedly mounted on the amplification base 301. Specifically, two fixed connecting wing screw fixing seats 308 are fixedly mounted on the lower part of the winglet beam amplification 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 winglet beam amplification base plate 302 through the motion connecting rod 310, and the lower end of the electric push rod 305 is fixedly connected to the amplification base 301 through the push rod base 306.

[0089] 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.

[0090] 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.

[0091] It is worth noting that when using the support column 2 to connect the folding wing fixing assembly 1 and the winglet bundle assembly 3, slots need to be cut on both sides of the lower end of the support column 2 to avoid the movement of the motion connecting rod 310.

[0092] During implementation, rotating the wing screw 309 allows it to insert into the safety positioning hole of the support column 2, which restricts the relative displacement between the wing assembly substrate 302 and the support column 2, thereby limiting the downward movement of the wing assembly 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 assembly substrate 302 to be moved under the action of the electric push rod 305, thus unlocking the wing.

[0093] In one specific embodiment of the present invention, such as Figure 5 , Figure 6 As shown, the vane beaming substrate 302 has an annular structure; the locking assembly 307 is provided in multiple sets and is circumferentially mounted on the vane beaming substrate 302.

[0094] 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.

[0095] 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.

[0096] Specifically, such as Figure 6 As shown, the guide shaft seat 3071 is fixedly installed below the blade bundle substrate 302.

[0097] 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.

[0098] 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.

[0099] 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.

[0100] 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.

[0101] 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.

[0102] 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.

[0103] Specifically, the T-shaped limiting groove 3072 includes a transverse groove and a longitudinal groove that are interconnected.

[0104] 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.

[0105] 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.

[0106] 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.

[0107] During implementation: 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.

[0108] 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.

[0109] 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.

[0110] 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.

[0111] Furthermore, the main electronic components of the testing device are housed inside the supporting column 2 and the cabinet 4. Due to the limited internal space of the supporting column 2, the cabinet 4 is used to house the electrical components of the testing circuit of this invention. Specifically, the supporting column 2 has a cylindrical structure with a central cavity that communicates with the internal space of the cabinet 4, facilitating cable routing.

[0112] This invention controls the testing device through a testing circuit, which consists of a control module, a display module, a detection module, and a power supply module. The power supply module is an AC / DC power supply, outputting +12V to power the detection and control modules. The detection module includes eight photoelectric sensors: 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. The control module includes a microprocessor and a timer. The timer captures the unlocking and positioning times of the four winglets. The microprocessor uses an STM32F103, initializes each functional module using STM32CubeMX, and is programmed using Keil C language on the MDK-ARM platform. The microprocessor calculates the deployment time based on the unlocking and positioning signals of winglets 1, 2, 3, and 4 detected by the detection module and drives the display module to display the information. The display module is a display window 201; it consists of five sets of LED digital tubes, capable of displaying the deployment time and asynchronous time of each winglet.

[0113] 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.

[0114] Table 1. Truth Table of State Logic for Photoelectric Sensors

[0115] 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

[0116] 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.

[0117] The measurement method employs a timer capture principle. Specifically, the unlocking and positioning signals of the four winglets are both rising edge signals after passing through the detection circuit, and are acquired by different channels of the timer. The unlocking signals output by the four unlocking photoelectric sensors 206 are detected by an OR gate circuit to start the timing, and the four unlocking signals are captured sequentially. When the positioning photoelectric sensor 102 receives the positioning signal, the timer captures the four positioning moments sequentially. The resulting pulse widths and durations T1, T2, T3, and T4 are the deployment times of each winglet. The maximum time difference in winglet release is the winglet release asynchronous time T. s The maximum time difference between the winglets deploying to their final positions is the winglet deployment asynchronous time T. e .

[0118] The wing deployment time Ti is the difference between the wing's arrival time and 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.

[0119] 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.

[0120] The wing deployment asynchronous time Te is the difference between the acquisition time of the last wing arrival signal and 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.

[0121] This invention features a winglet bundle assembly to ensure the synchronous deployment of four winglets. It employs a highly sensitive photoelectric sensor to measure the unlocking and positioning signals 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.

[0122] 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 device for the deployment consistency of a multi-bladed folding wing, characterized in that, include: Folding wing fixing assembly (1) and winglet bundle assembly (3); The winglet assembly includes: a folding wing fixing plate (101), a positioning photoelectric sensor (102), and a folding wing fixing base plate (104); the folding wing mechanism to be detected is clamped and fixed between the folding wing fixing base plate (104) and the folding wing fixing plate (101); the positioning photoelectric sensor (102) is used to monitor whether the winglets of the folding wing mechanism are unfolded into position; the winglet assembly (3) includes: an assembly base (301), a winglet assembly base plate (302), an electric push rod (305), and a locking assembly (307); the winglet assembly base plate (302) is provided with a locking assembly (307), the locking assembly (307) is used to lock or unlock the winglets of the folding wing mechanism; the electric push rod (305) is used to drive the winglet assembly base plate (302) to move; 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 installed below the winglet bundle substrate (302); the guide shaft (3073) is slidably installed inside the guide shaft seat (3071), and a return spring (3077) is provided between the two; the return spring (3077) is sleeved on the lower part of the guide shaft (3073); the locking pin (3074) is fixedly installed above the guide shaft (3073), and the locking pin (3074) is used to lock the winglet; the folding wing mechanism includes a main structure and a winglet; the winglet is rotatably installed on the main structure; the main structure is fixed by the folding wing fixing assembly (1). The wing can be bent downwards and limited by the locking pin (3074); when the locking pin (3074) limits the wing, the locking pin (3074) protrudes out of the wing bundle base plate (302) to block the wing from unfolding; the side of the guide shaft seat (3071) is provided with a T-shaped limiting groove (3072); a handle screw (3075) is fixedly installed on the guide shaft (3073), the handle screw (3075) is perpendicular to the guide shaft (3073) and extends out from the T-shaped limiting groove (3072); the T-shaped limiting groove (3072) includes a transverse groove and a longitudinal groove that are interconnected; 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 switching the locked state and unlocked state of the wing.

2. The multi-bladed folding wing deployment consistency testing device according to claim 1, characterized in that, When the folding wing mechanism is in the folded state, the wing bends downward and is limited by the locking assembly (307); when the wing bundle substrate (302) moves downward, the locking assembly (307) separates from the wing and releases the limitation on the wing.

3. The multi-bladed folding wing deployment consistency testing device according to claim 2, characterized in that, The folding wing fixing assembly (1) further includes: a sensor fixing bracket (103); a plurality of sensor fixing brackets (103) are arranged circumferentially on the folding wing fixing base plate (104); the positioning photoelectric sensor (102) is fixedly installed on the sensor fixing bracket (103).

4. The multi-bladed folding wing deployment consistency testing device according to claim 3, characterized in that, A screw is vertically arranged on the folding wing fixing base plate (104); a through hole is provided on the folding wing fixing pressure plate (101); the folding wing fixing pressure plate (101) is sleeved on the screw through the through hole, and a wing nut (105) is installed on the part of the screw protruding from the folding wing fixing pressure plate (101).

5. The multi-bladed folding wing deployment consistency testing device according to claim 4, characterized in that, The positioning photoelectric sensor (102) has a C-shaped structure with an indented groove.

6. The multi-bladed folding wing deployment consistency testing device according to claim 5, characterized in that, When the wing is deployed, it can be inserted into the groove of the positioning photoelectric sensor (102).

7. The multi-bladed folding wing deployment consistency testing device according to any one of claims 1-6, characterized in that, The wing-shaped beam-forming substrate (302) is slidably mounted on the beam-forming base (301) via a linear bearing (303) and a guide slide (304).

8. The multi-bladed folding wing deployment consistency testing device according to claim 7, characterized in that, The linear bearing (303) is fixedly mounted on the beam-forming base (301), and the guide slide (304) is fixedly mounted on the wing beam-forming substrate (302); the guide slide (304) is sleeved inside the linear bearing (303) and can slide relative to it.

9. The multi-bladed folding wing deployment consistency testing device according to claim 8, characterized in that, The wing-shaped beam-laying substrate (302) has a ring structure.

10. The multi-bladed folding wing deployment consistency testing device according to claim 9, characterized in that, The locking assembly (307) is provided in multiple sets and is circumferentially mounted on the wing bundle base plate (302).

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