Folding empennage unfolding performance test equipment and test method

Abstract

The invention relates to a folding empennage unfolding performance test device and method, and the device comprises a pedestal, the top surface of the pedestal is provided with an installation groove for installing an empennage cabin, the groove opening of the installation groove is uniformly provided with a plurality of empennage grooves for placing an unfolded empennage in the circumferential direction, and each empennage groove is internally provided with a laser sensor; all the laser sensors are located at the same height; the motor base is located below the base, and a motor is arranged in the motor base and used for driving the base to drive the empennage cabin to rotate; the hammering mechanism comprises a hammering seat, the hammering seat is arranged over the empennage cabin, and a preset distance is reserved between the hammering seat and the empennage cabin; and the controller is electrically connected with the motor and the hammering mechanism, controls the rotating speed of the empennage cabin through the motor, and controls the hammering seat to beat the locking mechanism of the empennage cabin and unfold the empennage if the empennage cabin reaches the specified rotating speed. According to the invention, the unfolding process of the folding empennage in the flight state of the aircraft can be simulated in a limited space, and the unfolding performance of the folding empennage can be effectively evaluated.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of equipment performance test, in particular to a folding tail wing unfolding performance test device and test method. BACKGROUND

[0002] In order to miniaturize the aircraft launching device, facilitate transportation and storage, the aircraft largely adopts box (cylinder) type launching. The folding tail wing can reduce the size of the aircraft, facilitate storage and launching, thereby improving the tactical and technical performance of the aircraft system, and has been widely used in modern aircraft. Under normal circumstances, the folding tail wing is folded and adapted to the inner wall of the launching box (cylinder) and stored in the launching box (cylinder). After the aircraft is launched out of the launching box (cylinder), the folding tail wing is automatically unfolded to the position under the action of the driving force and locked. The folding tail wing of the box type launching is in a folded state before launching, and is unfolded rapidly and reliably at the moment of launching, thereby generating a stable moment to ensure the stable flight of the aircraft. Therefore, the unfolding time and synchronism of the folding tail wing not only have an important influence on the flight stability, but also have a great influence on the design of the launching device, the range and the density.

[0003] In order to ensure the unfolding time and synchronism of the folding tail wing, it is necessary to carry out unfolding test on the folding tail wing, simulate the rotation and overload environment of the folding tail wing in the launching device, and test the unfolding performance of the folding tail wing. In the prior art, air gun launching simulation test bullets are used, and the unfolding of the folding tail wing of the simulation test bullets in the flight process is recorded by a high-speed camera to complete the unfolding performance test of the folding tail wing. Although this method has true and reliable results, it is relatively troublesome to arrange the site and needs a large enough space, and also lacks a certain safety. SUMMARY

[0004] The present application provides a folding tail wing unfolding performance test device and test method, which can simulate the unfolding process of the folding tail wing in the flight state of the aircraft in a limited space, and effectively evaluate the unfolding performance of the folding tail wing.

[0005] In a first aspect, the present application provides a folding tail wing unfolding performance test device, comprising: a base, a mounting groove for mounting a tail wing cabin is formed in the top surface of the base, a plurality of tail wing grooves for placing the unfolded tail wing are uniformly formed in the groove opening of the mounting groove in the circumferential direction, a laser sensor is installed in each tail wing groove, and all the laser sensors are at the same height; a motor seat is located below the base, a motor is arranged in the motor seat for driving the base to rotate the tail wing cabin; a hammering mechanism comprises a hammering seat, the hammering seat is arranged directly above the tail wing cabin and has a predetermined distance from the tail wing cabin; a controller is electrically connected with the motor and the hammering mechanism, respectively, the rotational speed of the tail wing cabin is controlled by the motor, and if the tail wing cabin reaches the specified rotational speed, the hammering seat is controlled to hit the locking mechanism of the tail wing cabin to unfold the tail wing.

[0006] In some embodiments in combination with the first aspect, there is a gap between the base and the motor base.

[0007] In some embodiments in combination with the first aspect, the bottom of the tail wing cabin is fixedly installed in the installation slot, the motor shaft of the motor is fixedly connected with the base, the motor drives the base and the tail wing cabin to rotate synchronously, and no relative displacement is generated between the base and the tail wing cabin.

[0008] In some embodiments in combination with the first aspect, the height of the groove bottom of the tail wing slot is lower than the horizontal height of the unfolded tail wing.

[0009] In some embodiments in combination with the first aspect, the laser sensor comprises a laser emitter and a laser receiver, both of which are at the same height and are respectively arranged on a group of opposite side walls of the corresponding tail wing slot, and the unfolded tail wing is located between the laser emitter and the laser receiver.

[0010] In some embodiments in combination with the first aspect, a support is installed on the top of the base, the hammering seat is installed on the top of the support, and a preset distance is left between the hammering seat and the tail wing cabin.

[0011] In some embodiments in combination with the first aspect, the support comprises two symmetrically arranged support arms, both ends of the support arms are connected with the hammering seat and the base respectively, and the connection point of the support arms and the base is located in the interval area between adjacent two tail wing slots.

[0012] In some embodiments in combination with the first aspect, the support arms are connected with the hammering seat and the base by threads.

[0013] In some embodiments in combination with the first aspect, the hammering mechanism further comprises a driving device, the driving device is electrically connected with the controller, the controller controls the lifting of the hammering seat through the driving device, and the locking mechanism of the tail wing cabin is struck.

[0014] In the second aspect, the application provides a test method based on the folding tail wing unfolding performance test equipment in any of the above embodiments, which comprises the following steps: starting the motor by the controller to drive the base to rotate synchronously with the tail wing cabin; controlling the motor speed by the controller to adjust the specified rotating speed of the tail wing cabin, the controller controls the hammering seat to strike the locking mechanism of the tail wing cabin, all tail wings are unfolded and respectively enter the tail wing slots; recording the time when each tail wing enters the tail wing slot according to the laser sensor in each tail wing slot, and determining the unfolding performance of the tail wing.

[0015] The technical scheme provided by the embodiments of the application has the following beneficial effects: In this application, the folding tail fin deployment performance testing equipment aims to simulate the rotational and overload environment experienced by the tail fin compartment within the launch box (tube) to test the tail fin's deployment performance. By providing a mounting slot on the top surface of the base for installing the tail fin compartment, the tail fin compartment can be effectively fixed within the base. By placing the motor within a motor mount, the motor's position can be effectively fixed, maintaining its stability during rotation. By placing the base directly above the motor mount, with the motor electrically connected to the controller, the base is driven by the motor to rotate the tail fin compartment. Simultaneously, adjusting the motor's speed adjusts the tail fin compartment's rotational speed, thereby simulating the aircraft's rotational environment within the launch box (tube) and after launch.

[0016] Because the tail fins of the tail fin compartment remain folded under the locking mechanism until the tail fin compartment reaches the specified rotational speed, the overload environment inside the launch device is simulated before the tail fin compartment reaches the specified rotational speed. By observing whether the tail fins of the tail fin compartment deploy in advance, the locking performance of the locking mechanism can be effectively judged. When the tail fin compartment reaches the specified rotational speed, the overload and overload relief environment inside the launch box (tube) is simulated by striking the locking mechanism with a hammer seat located directly above the tail fin compartment. All tail fins deploy, and the entry time of the corresponding tail fin is recorded by laser sensors in the tail fin slots on the base, thereby testing the deployment performance of the tail fins.

[0017] Using the folding tail fin deployment measurement device provided in this embodiment for ground testing instead of actual launch flight tests can provide data support for launch flight tests within a limited space. It can simulate the deployment process of the folding tail fin in the flight state of the aircraft more realistically, effectively evaluate the deployment performance of the folding tail fin, reduce the risk of aircraft flight tests, and save a lot of test costs. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of the folding tail fin deployment measuring device in the embodiments of this application; Figure 2 for Figure 1 A schematic diagram of the structure after the installation of the mid-folding tail fin deployment measurement equipment and the tail fin compartment; Figure 3 This is a flowchart of the testing method for the folding tail fin deployment performance testing equipment in the embodiments of this application.

[0019] In the picture: 1. Motor mount; 2. Base; 21; Tail wing slot; 3. Tail fin compartment; 31. Tail fin; 32. Locking mechanism; 4. Hammering seat; 5. Bracket; 51. Support arm. Detailed Implementation

[0020] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present application.

[0021] A tail fin compartment is a structural component in aircraft or rockets used to mount the tail fin. Its main function is to provide mounting space for the tail fin and enhance flight stability. In this application, the tail fin is a folding tail fin; therefore, the tail fin compartment of this application also functions to store the folding tail fin and deploy it when needed.

[0022] This application provides a folding tail fin deployment performance testing device and method, which can simulate the deployment process of a folding tail fin in flight within a limited space, effectively evaluating the deployment performance of the folding tail fin.

[0023] Firstly, this application provides a device for testing the deployment performance of a folding tail fin.

[0024] See Figure 1 and Figure 2 , Figure 1 This is a schematic diagram of the structure of the folding tail fin deployment measuring device in the embodiments of this application; Figure 2 for Figure 1 A schematic diagram of the structure after the mid-folding tail fin deployment measurement equipment and tail fin compartment 3 are installed. (See diagram below.) Figure 1 and Figure 2 As shown, in one embodiment, the folding tail fin deployment performance testing device includes a base 2, a motor mount 1, a hammer impact mechanism, and a controller. Specifically, the top surface of the base 2 has a mounting groove for mounting the tail fin compartment 3. Multiple tail fin slots 21 are evenly distributed circumferentially at the opening of the mounting groove for placing the deployed tail fin 31. Each tail fin slot 21 is equipped with a laser sensor, and all laser sensors are at the same height.

[0025] The base 2 and the tail fin compartment 3 are identical in design. The tail fins 31 are hinged to the tail fin compartment 3. The number of tail fins 31 mounted on the tail fin compartment 3 can be eight, corresponding to eight tail fin slots 21. When folded, all eight tail fins 31 are gathered together inside the tail fin compartment 3; when unfolded, the eight tail fins 31 enter their respective tail fin slots 21, and laser sensors within each tail fin slot 21 record the time of entry of the corresponding tail fin 31. Figure 1 Looking at it from above, the tail fin slot 21 is a rectangular slot, and the deployed tail fin 31 contacts the bottom of the slot.

[0026] The motor mount 1 can be placed on the ground or a workbench, ensuring it is horizontal. The motor mount 1 is located below the base 2 and houses a motor, which can be a brushless DC motor with adjustable speed. The motor rotor and base 2 can be fixedly connected or integrated. The motor rotor drives the base 2 to rotate, thereby rotating the tail fin compartment 3 within the base 2. The controller is electrically connected to the motor, controlling the rotational speed of the tail fin compartment 3 via the motor.

[0027] The hammering mechanism includes a hammering seat 4, which is located directly above the tail fin compartment 3 and opposite to the locking mechanism 32 of the tail fin compartment 3. A preset distance is left between the hammering mechanism and the tail fin compartment 3 (locking mechanism 32). The hammering mechanism is electrically connected to the controller. If the motor controls the rotation speed of the tail fin compartment 3 to reach the specified speed, the controller controls the hammering seat 4 to strike the locking mechanism 32 of the tail fin compartment 3, unfolding the tail fin 31 so that the tail fin 31 enters the tail fin slot 21. The laser sensor in each tail fin slot 21 records the time when the corresponding tail fin 31 enters.

[0028] In this embodiment, the folding tail fin deployment performance testing equipment is designed to simulate the rotational and overload environment experienced by the tail fin compartment 3 within the launch box (tube) to test the deployment performance of the tail fin 31. By providing a mounting slot for installing the tail fin compartment 3 on the top surface of the base 2, the tail fin compartment 3 can be effectively fixedly installed within the base 2. By placing the motor within the motor mount 1, the position of the motor can be effectively fixed, maintaining its stability during rotation.

[0029] By placing the base 2 directly above the motor base 1, the motor is electrically connected to the controller, and the motor drives the base 2 to rotate the tail fin compartment 3. At the same time, the speed of the motor is adjusted, thereby adjusting the speed of the tail fin compartment 3, thus simulating the rotational overload environment of the aircraft inside the launch box (tube) and after launch.

[0030] Because the tail fins 31 of the tail fin compartment 3 are always folded under the action of the locking mechanism 32 before the tail fin compartment 3 reaches the specified rotational speed, the overload environment of the tail fin compartment 3 in the launch device is simulated before the tail fin compartment 3 reaches the specified rotational speed. By observing whether the tail fins 31 of the tail fin compartment 3 are deployed in advance, the locking performance of the locking mechanism 32 can be effectively judged. When the tail fin compartment 3 reaches the specified rotational speed, the overload and overload disappearance environment in the launch box (tube) can be simulated by striking the locking mechanism 32 with the hammer seat 4 set directly above the tail fin compartment 3. All tail fins 31 are deployed. The laser sensors in each tail fin slot 21 on the base 2 record the entry time of the corresponding tail fin 31, thereby testing the deployment performance of the tail fins 31.

[0031] Multiple tail fin slots 21 are circumferentially formed at the opening of the mounting slot to accommodate the deployed tail fin 31. Each tail fin slot 21 is equipped with a laser sensor, and all laser sensors are at the same height to ensure sufficient deployment space for the tail fin 31. The laser sensors can also effectively record the entry time of the corresponding tail fin 31. The hammer base 4 is positioned directly above the tail fin compartment 3, with a gap between them. This serves two purposes: firstly, it avoids interfering with the rotation of the tail fin compartment 3 by the motor-driven base 2; secondly, it allows the locking mechanism 32 of the tail fin compartment 3 to be struck immediately when the tail fin compartment 3 reaches the specified rotation speed, thus enabling the tail fin compartment 3 to deploy the tail fin 31 promptly.

[0032] Using the folding tail fin deployment measurement device provided in this embodiment for ground testing instead of actual launch flight tests can provide data support for launch flight tests within a limited space. It can simulate the deployment process of the folding tail fin in the flight state of the aircraft more realistically, effectively evaluate the deployment performance of the folding tail fin, reduce the risk of aircraft flight tests, and save a lot of test costs.

[0033] Furthermore, in one embodiment, such as Figure 2 As shown, there is a gap between the base 2 and the motor mount 1. In this embodiment, the above technical solution ensures that when the motor drives the base 2 to rotate the tail wing 3, the gap can avoid friction and jamming caused by direct contact between the base 2 and the motor mount 1.

[0034] Furthermore, in one embodiment, such as Figure 2 As shown, the bottom of the tail fin compartment 3 is fixedly installed in the mounting groove. The motor shaft of the motor is fixedly connected to the base 2. The motor drives the base 2 and the tail fin compartment 3 to rotate synchronously without relative displacement. In this embodiment, the mounting groove on the top surface of the base 2 precisely matches the bottom of the tail fin compartment 3, forming a circumferential limit to ensure accurate installation. Multiple fastening bolts or locating pins can be used, passing through the through holes at the bottom of the tail fin compartment 3 and connecting to the threaded holes at the bottom of the mounting groove to form a rigid fixation. Alternatively, a boss or keyway can be provided on the side of the mounting groove to engage with the groove or key at the bottom of the tail fin compartment 3 to prevent circumferential displacement of the tail fin compartment 3 during rotation. The motor shaft of the motor is fixedly connected to the base 2 through a coupling (e.g., diaphragm coupling, gear coupling, etc.), which can withstand high torque and achieve zero backlash transmission. The motor shaft and the base 2 are precision interference fit, and further locked with set screws or nuts to eliminate any possible relative displacement, ensuring that the motor drives the base 2 and the tail fin compartment 3 to rotate synchronously, and that the two do not produce relative displacement, simulating the real state of the tail fin 31 rotating synchronously with the missile body when the aircraft is launched, and ensuring that the centrifugal force field is consistent with the actual launch environment.

[0035] Furthermore, in one embodiment, the bottom height of the tail fin slot 21 is lower than the horizontal height of the deployed tail fin 31. In this embodiment, after the tail fin 31 is unlocked from the folded state, it needs to be rotated outward to the horizontally deployed position and locked. The bottom of the slot is lower than the height of the deployed tail fin 31, providing sufficient vertical accommodation space. This avoids rigid collisions or friction between the tail fin 31 and the bottom of the slot when it is deployed, ensuring that the tail fin 31 can be fully deployed and stably locked, replicating the working attitude of the tail fin 31 after actual launch, and laying the foundation for the authenticity of the test data.

[0036] Furthermore, in one embodiment, the laser sensor includes a laser emitter and a laser receiver, both at the same height and respectively disposed on a set of opposite sidewalls of the corresponding tail fin slot 21, with the deployed tail fin 31 located between the laser emitter and the laser receiver. In this embodiment, the laser sensor utilizes the principle of rectilinear propagation and blocking of light, determining whether the tail fin 31 has deployed to its full position and the timing of its deployment by detecting the obstruction of the laser beam by the tail fin 31. The laser sensor includes a laser emitter and a laser receiver; the laser emitter emits a laser beam, and the laser receiver receives the laser beam. By setting the laser emitter and laser receiver at the same height and respectively disposed on a set of opposite sidewalls of the corresponding tail fin slot 21, with the deployed tail fin 31 located between the laser emitter and the laser receiver, the relative position of the laser beam and the tail fin 31 is ensured to be constant and unaffected by overall equipment vibration. When the tail fin compartment 3 rotates at high speed, the laser beam always illuminates the tail fin 31 perpendicularly, ensuring that the deployment state of the tail fin 31 can be accurately detected at any rotation angle, unaffected by centrifugal force. At the moment when the laser beam is blocked by the tail fin 31, the laser receiver generates a signal change, and the controller can accurately record the time when the tail fin 31 enters the corresponding tail fin slot 21.

[0037] Furthermore, in one embodiment, such as Figure 1 As shown, a bracket 5 is mounted on the top of the base 2, and a hammer-shaped base 4 is mounted on the top of the bracket 5. A preset distance is maintained between the hammer-shaped base 4 and the tail fin compartment 3. In this embodiment, the bracket 5 is mounted on the top of the base 2, and the hammer-shaped base 4 is mounted on the top of the bracket 5, so that the motor drives the base 2 to rotate, causing the tail fin compartment 3 and the hammer-shaped base 4 to rotate synchronously. When the predetermined speed is reached, the hammer-shaped base 4 aligns with the locking mechanism 32 of the tail fin compartment 3, and accurately strikes the locking mechanism 32 with the impact force generated at the preset distance. This does not affect the motor driving the base 2 to rotate the tail fin compartment 3, and also allows the tail fin compartment 3 to deploy the tail fin 31 in time.

[0038] Furthermore, in one embodiment, the support 5 includes two symmetrically arranged support arms 51. The two ends of each support arm 51 are connected to the hammer base 4 and the base 2, respectively, and the connection point between the support arm 51 and the base 2 is located in the interval area between two adjacent tail fin slots 21. In this embodiment, by symmetrically arranging the two support arms 51, the base 2 maintains balance during rotation; by connecting the two ends of each support arm 51 to the hammer base 4 and the base 2, the base 2 rotates synchronously with the hammer base 4; and the connection point with the base 2 is precisely located in the interval area between two adjacent tail fin slots 21, effectively avoiding the deployment path of the tail fin 31.

[0039] Furthermore, in one embodiment, the support arm 51 is threadedly connected to the hammer seat 4 and the base 2. In this embodiment, both ends of the support arm 51 are machined with external threads, which precisely mate with the internal threaded holes on the hammer seat 4 and the base 2, respectively, achieving rapid tightening through rotation. Furthermore, since the two support arms 51 are symmetrically distributed about the center of the base 2, rotational balance and uniform load distribution are ensured.

[0040] Furthermore, in one embodiment, the hammer-striking mechanism further includes a drive device electrically connected to a controller. The controller controls the raising and lowering of the hammer base 4 via the drive device to strike the locking mechanism 32 of the tail fin compartment 3. In this embodiment, the hammer-striking mechanism also includes a drive device electrically connected to the controller. The drive device can be a pneumatic drive device, including a solenoid valve, a pressure source, a pneumatic actuator, an air passage, and a seal. The solenoid valve is internally located in the hammer base 4 and controls the opening and closing of the air passage. The pneumatic actuator can be a compressed air tank or an air pump, providing the pneumatic power to drive the hammer base 4. The pneumatic actuator can be a cylinder or a pneumatic piston, converting pneumatic energy into mechanical downward force to push the hammer base 4 down. The pneumatic pipeline is used to transmit compressed air, and the seal ensures stable air pressure.

[0041] The controller can precisely adjust the lifting height, descent speed, and impact force of the hammer 4 via the drive device, ensuring consistent energy and stroke for each strike to the locking mechanism 32 of the tail fin compartment 3. Furthermore, for different tail fin locking mechanisms 32 (such as those requiring different unlocking forces), parameters can be preset via the controller, eliminating the need for mechanical modifications and improving equipment adaptability.

[0042] Secondly, this application provides a testing method for the folding tail wing deployment performance testing device based on any of the above embodiments.

[0043] See Figure 3 , Figure 3 This is a flowchart illustrating the testing method of the folding tail fin deployment performance testing equipment in an embodiment of this application. Figure 3 As shown, in one embodiment, the testing method of the folding tail fin deployment performance testing equipment includes: Step S10: Start the motor via the controller to drive the base 2 to rotate the tail wing compartment 3 synchronously.

[0044] In step S20, the controller controls the motor speed to adjust the tail fin compartment 3 to a specified speed. The controller controls the hammer base 4 to strike the locking mechanism 32 of the tail fin compartment 3, so that all tail fins 31 are deployed and enter the tail fin slots 21 respectively.

[0045] Step S30: Determine the deployment performance of the tail wing 31 based on the entry time of the corresponding tail wing 31 recorded by the laser sensor in each tail wing slot 21.

[0046] In this embodiment, the controller sends a start command to the motor, and the motor output torque is transmitted to the base 2 through the motor shaft (the motor shaft is rigidly fixed to the base 2). The bottom of the tail fin compartment 3 is fixed to the mounting slot of the base 2 and rotates synchronously with the base 2 to form a centrifugal force field consistent with the launch of the aircraft. At the same time, the speed of the motor is adjusted, thereby adjusting the speed of the tail fin compartment 3, thus simulating the rotational overload environment of the aircraft inside the launch box (tube) and after launch.

[0047] The controller collects the motor speed signal in real time and controls the motor speed to adjust the tail fin compartment 3 to a specified speed (simulating the rotational overload state during aircraft launch). The controller immediately sends a command to the drive device of the hammer striking mechanism, driving the hammer striking base 4 to descend vertically and accurately strike the locking mechanism 32 of the tail fin compartment 3. After the locking mechanism 32 is unlocked, all tail fins 31 rotate outward under the action of centrifugal force and their own deployment driving force, and finally enter the corresponding tail fin slot 21. The tail fin slot 21 provides a limit for the tail fins 31 to ensure that they are deployed in place.

[0048] The laser sensor in each tail fin slot 21 records the time when the corresponding tail fin 31 enters. By comparing the time corresponding to each tail fin 31, the deployment performance of the tail fin 31 is accurately judged from two aspects: the deployment time of a single tail fin 31 (i.e., the time from when the hammer 4 strikes the locking mechanism 32 to when the tail fin 31 enters the corresponding tail fin slot 21) and the synchronicity of all tail fins 31 (i.e., the difference in the deployment time of each tail fin 31).

[0049] The test method of the folding tail deployment measurement device provided in this embodiment can be used for ground testing instead of actual launch flight tests. It can provide data support for launch flight tests in a limited space, simulate the deployment process of the folding tail in the flight state of the aircraft more realistically, effectively evaluate the deployment performance of the folding tail, reduce the risk of aircraft flight tests, and save a lot of test costs.

[0050] In the description of this application, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.

[0051] It should be noted that in this application, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0052] The above description is merely a specific embodiment of this application, enabling those skilled in the art to understand or implement this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A device for testing the deployment performance of a folding tail fin, characterized in that, include: The base (2) has an installation slot on its top surface for installing the tail wing compartment (3). Multiple tail wing slots (21) for placing the deployed tail wing (31) are evenly provided around the opening of the installation slot. Each tail wing slot (21) is equipped with a laser sensor, and all laser sensors are at the same height. The motor mount (1) is located below the base (2). The motor mount (1) contains a motor for driving the base (2) to rotate the tail fin compartment (3). The hammering mechanism includes a hammering seat (4), which is located directly above the tail fin compartment (3) and is at a predetermined distance from the tail fin compartment (3). The controller is electrically connected to the motor and the hammering mechanism respectively. It controls the rotation speed of the tail fin compartment (3) through the motor. If the tail fin compartment (3) reaches the specified rotation speed, it controls the hammering seat (4) to strike the locking mechanism (32) of the tail fin compartment (3) and unfold the tail fin (31).

2. The folding tail fin deployment performance testing equipment as described in claim 1, characterized in that, There is a gap between the base (2) and the motor base (1).

3. The folding tail fin deployment performance testing equipment as described in claim 1, characterized in that, The bottom of the tail fin compartment (3) is fixedly installed in the mounting slot. The motor shaft of the motor is fixedly connected to the base (2). The motor drives the base (2) and the tail fin compartment (3) to rotate synchronously, and the two do not produce relative displacement.

4. The folding tail fin deployment performance testing equipment as described in claim 1, characterized in that, The bottom of the tail fin groove (21) is lower than the horizontal height of the deployed tail fin (31).

5. The folding tail fin deployment performance testing equipment as described in claim 1, characterized in that, The laser sensor includes a laser emitter and a laser receiver, which are at the same height and are respectively set on a set of opposite sidewalls of the corresponding tail fin slot (21), and the deployed tail fin (31) is located between the laser emitter and the laser receiver.

6. The folding tail fin deployment performance testing device as described in claim 1, characterized in that, The base (2) is equipped with a bracket (5) on top, and the hammer seat (4) is installed on top of the bracket (5). A preset distance is left between the hammer seat (4) and the tail fin compartment (3).

7. The folding tail fin deployment performance testing device as described in claim 6, characterized in that, The bracket (5) includes two symmetrically arranged support arms (51), the two ends of which are connected to the hammer seat (4) and the base (2) respectively, and the connection point between the support arm (51) and the base (2) is located in the interval area between two adjacent tail fin slots (21).

8. The folding tail fin deployment performance testing device as described in claim 7, characterized in that, The support arm (51) is threadedly connected to the hammer seat (4) and the base (2).

9. The folding tail fin deployment performance testing device as described in claim 7, characterized in that, The hammering mechanism also includes a drive device, which is electrically connected to the controller. The controller controls the lifting and lowering of the hammer base (4) through the drive device to strike the locking mechanism (32) of the tail fin compartment (3).

10. A testing method based on the folding tail fin deployment performance testing equipment according to any one of claims 1-9, characterized in that, include: The motor is started by the controller, which drives the base (2) to rotate synchronously with the tail fin compartment (3); The controller controls the motor speed to adjust the tail fin compartment (3) to the specified speed. The controller controls the hammer seat (4) to strike the locking mechanism (32) of the tail fin compartment (3), so that all tail fins (31) are deployed and enter the tail fin slot (21) respectively. The deployment performance of the tail fin (31) is determined by recording the entry time of the corresponding tail fin (31) by the laser sensor in each tail fin slot (21).

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