Automatic rotation reliability evaluation and test mechanism for rudder rotary actuator

Abstract

An automatic rotation reliability evaluation and test mechanism for a rudder rotary actuator comprises an automatic rotating system, a state maintaining and releasing system, a measuring system, and a control system, wherein the automatic rotating system provides rotational power and enables power transmission, and the automatic rotating system comprises a direct current motor, a controller (1), a dynamic torque sensor (3), a rocker arm mechanism (6), and a base tooling (7); the state maintaining and releasing system allows the direct current motor and the controller (1) to rotate to a fixed angle and maintain the rudder rotary actuator at this angle for a certain period of time, and then return to the original angle; and the measurement control system comprises an angle sensor (5) and a data collector, the data collector, the direct current motor and the controller (1) being all electrically connected to the control system. Automatic deployment and retraction of the rudder rotary actuator under real operating conditions can be simulated, and the degradation of torque load over time is obtained, thereby providing data support for reliability evaluation of the rudder rotary actuator.

Description

A test mechanism for evaluating the reliability of automatic rotation of a rudder blade rotary actuator Technical Field

[0001] The present invention relates to a reliability evaluation test mechanism, more particularly to an automatic rotation reliability evaluation test mechanism for a rudder blade rotating actuator. Background Art

[0002] The rudder blade rotating actuator is the core mechanism of the folding rudder, and its main function is to drive the folding rudder blade to unfold. The actuator cylinder type unfolding system of the folding rudder blade mainly includes the actuator cylinder, unfolding actuator and folding wings. The commonly used unfolding actuators are direct connection type, linkage slider type and gear-rack type. The working principles of each system are as follows: (1) Direct connection type, the actuator cylinder is connected to the missile body through a hinge, and the wings are connected to the piston rod through a hinge and rotated and folded on the back of the missile. During operation, the high-temperature and high-pressure gas inside the actuator cylinder pushes the piston rod to move along the slide and drives the wings to unfold around the rotation axis. Its structure has the characteristics of using an integral wing and a simple structure. (2) Linkage slider type, the two wings are symmetrically folded on both sides of the wings. During operation, the piston rod pushes the linkage slider, and the slider pushes the two wings to unfold around the rotation axis through a two-point hinge connection; its structure has the characteristics of a compact transmission mechanism and low friction resistance. (3) Gear-rack type, the unfolding process is similar to the linkage slider type, and the transmission mechanism of the piston and the wings adopts a gear-rack group. Compared with the above two methods, the gear-rack transmission deployment mechanism has the advantages of high transmission efficiency, high motion reliability, stable deployment process and low terminal speed.

[0003] During actual operation, the rudder blade rotary actuator will experience folding and unfolding. To ensure that the rudder blade rotary actuator can meet the requirements of rotation every time it works, it is necessary to assess whether its design and structure meet the reliability design indicators. Therefore, it is particularly important to simulate the actual tooling state of the rotary actuator and conduct a reliability assessment on the rudder blade rotary actuator. In order to conduct a reliability assessment of the rotary actuator, it is necessary to simulate its actual working state and conduct multiple fatigue tests to obtain the degradation relationship of its torque over time period, so as to accurately conduct reliability assessment work. However, the existing equipment does not have the test capabilities to carry out automatic rotation of the rotary actuator and obtain reliability assessment parameters.

[0004] Summary of the Invention

[0005] The purpose of the present invention is to provide a test mechanism for evaluating the reliability of automatic rotation of a rudder blade rotating actuator in response to the problems existing in the prior art.

[0006] To achieve the above-mentioned purpose, the technical solution of the present invention is: a test mechanism for the automatic rotation reliability evaluation of a rudder blade rotating actuator, comprising an automatic rotation system, a state holding and releasing system, a measuring system and a control system; the automatic rotation system provides rotational power and realizes power transmission, and the automatic rotation system comprises a DC motor and a controller, a dynamic torque sensor, a rocker mechanism and a base tooling, the DC motor and the controller can realize forward and reverse rotation and speed regulation functions, and also have a deceleration and braking function, the DC motor and the controller are connected to the dynamic torque sensor, the dynamic torque sensor outputs torque to the force transmission rod on the rocker mechanism, the rocker mechanism is directly connected to the rudder blade rotating actuator, and the rudder blade rotating actuator is fixedly mounted on the base On the tooling, rotational force is provided by the forward and reverse rotation of the DC motor and the controller, and then the rotational force is transmitted through the force transmission rod on the rocker mechanism, thereby realizing the horizontal transmission of the entire torque; the state holding release system enables the DC motor and the controller to maintain the state of the rudder blade rotating actuator at this angle after rotating to a fixed angle, and realizes the angle return of the rudder blade rotating actuator after maintaining this state for a certain period of time; the measurement and control system includes an angle sensor and a data collector, and the dynamic torque sensor and the angle sensor are both connected to the data collector. The data collector obtains the changes in torque load during multiple actions while monitoring the angle in real time. The data collector, DC motor and controller are all electrically connected to the control system.

[0007] The state holding release system includes an electromagnet mechanism, a fixed disc, an electromagnet sensing block, a stop latch, an initial proximity sensor, a termination proximity sensor, and a proximity sensing latch. The proximity sensing latch is connected to the rocker mechanism, and the stop latch, the initial proximity sensor, and the termination proximity sensor are installed on the fixed disc. The fixed disc is connected to the base tooling, and the electromagnet sensing block is installed on the rocker mechanism. The electromagnet mechanism includes an electromagnet, which is a key component for torque holding and torque release. The contact surface of the electromagnet can be adjusted and adapted to fit the electromagnet sensing block. The electromagnet, stop latch, initial proximity sensor, termination proximity sensor, and proximity sensing latch are all electrically connected to the control system; in the initial state, the stop latch is in contact with the card on the rocker mechanism. The contact of the electromagnet and the electromagnetic sensing block is to prevent excessive angle movement; when the system is running, the proximity sensing pin contacts the initial proximity sensor, and the initial proximity sensor transmits the signal to the DC motor and the controller, and the DC motor and the controller move in the opposite direction. When the electromagnet sensing block reaches the terminal state angle in rotation, the proximity sensing pin contacts the terminal proximity sensor, and the DC motor and the controller stop. At the same time, the electromagnet contacts the electromagnet sensing block and is electrically attracted. At this time, the rotation angle can be maintained. After the maintenance is completed, the electromagnet sensing block loses power and releases the electromagnet sensing block. The force transmission rod on the rocker mechanism performs free release movement when there is no load through the annular hole on the rotation transmission flange. At this time, the rotation angle can be automatically reset, which can completely simulate the state of the rudder rotary actuator when it is freely released.

[0008] The electromagnet is fixed on the angle adjustment bracket fixture, and the angle of the contact surface of the electromagnet is adjusted through the angle adjustment bracket fixture, so that the contact surface of the electromagnet can be adjusted and adapted to fit the electromagnet sensing block on the rocker arm mechanism.

[0009] The DC motor and the controller are connected to the torque input end of the dynamic torque sensor through a coupling.

[0010] The torque output end of the dynamic torque sensor is provided with a circular flange, the circular flange is connected to a rotation transmission flange, the rotation transmission flange is connected to the force transmission rod on the rocker mechanism, the torque output end of the dynamic torque sensor outputs torque, and the dynamic torque sensor outputs the torque to the force transmission rod on the rocker mechanism through the annular hole on the rotation transmission flange.

[0011] The force transmission rod on the rocker mechanism is aligned with the annular hole on the rotation transmission flange at the initial position.

[0012] The rocker mechanism is directly connected to the rudder blade rotating actuating cylinder through a keyway hole, and the rudder blade rotating actuating cylinder is fixedly mounted on the base tooling through the keyway hole.

[0013] The DC motor and the controller are fixedly mounted on the horizontal motor base through mounting holes.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] This test facility can simulate the automatic deployment and closing actions of the rudder blade rotary actuator under actual working conditions, and obtain the changing relationship between the torque load and time degradation during multiple actions, providing data support for the reliability assessment of the rudder blade rotary actuator, and making up for the shortcomings of existing equipment and technical capabilities. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] FIG1 is a top view of the present invention.

[0017] FIG2 is a perspective view of the present invention.

[0018] FIG3 is a side view of the present invention.

[0019] FIG4 is a schematic structural diagram of the rocker arm mechanism of the present invention.

[0020] FIG5 is a schematic diagram of the structure of the electromagnet mechanism in the present invention.

[0021] FIG6 is a schematic structural diagram of the rocker arm mechanism of the present invention.

[0022] FIG7 is a schematic diagram of the structure of the rotation transmission flange in the present invention.

[0023] In the figure, there are a DC motor and controller 1, a coupling 2, a dynamic torque sensor 3, a rotation transmission flange 4, an angle sensor 5, a rocker mechanism 6, a base tooling 7, an electromagnet mechanism 8, a fixed disc 9, an electromagnet sensing block 10, an electromagnet 11, a stop pin 12, an initial proximity sensor 13, an end proximity sensor 14, an angle adjustment bracket tooling 15, and a proximity sensing pin 16. DETAILED DESCRIPTION

[0024] The present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

[0025] Referring to Figures 1 to 4, a reliability evaluation test mechanism for automatic rotation of a rudder blade rotating actuator cylinder is a reliability evaluation test mechanism that simulates the automatic expansion and automatic closure of the rudder blade rotating actuator cylinder under actual working conditions; a reliability evaluation test mechanism for automatic rotation of a rudder blade rotating actuator cylinder is characterized in that it includes an automatic rotation system, a state holding release system, a measurement system and a control system.

[0026] Referring to Figures 1 to 4 , the automatic rotation system provides rotational power and achieves power transmission. The automatic rotation system includes a DC motor and controller 1, a dynamic torque sensor 3, a rocker mechanism 6, and a base assembly 7. The DC motor and controller 1 is a DC signal motor, fixedly mounted on a horizontal motor base via four mounting holes. The DC motor and controller 1 can achieve forward and reverse rotation, speed regulation, and deceleration braking. The DC motor and controller 1 is connected to the dynamic torque sensor 3, which outputs torque to the dowel rod of the rocker mechanism 6. Specifically, the DC motor and controller 1 is connected to the torque input end of the dynamic torque sensor 3 via a coupling 2. The torque output end of the dynamic torque sensor 3 is provided with a circular flange, which is screwed to a rotation transmission flange 4. The rotation transmission flange 4 is connected to the dowel rod of the rocker mechanism 6. The dynamic torque sensor 3 outputs torque at its torque output end, and the dynamic torque sensor 3 transmits torque to the dowel rod of the rocker mechanism 6 through an annular hole in the rotation transmission flange 4. The rocker mechanism 6 is directly connected to the rudder blade rotation actuator cylinder, and the rudder blade rotation actuator cylinder is fixedly mounted on the base tooling 7; specifically, the rocker mechanism 6 is directly connected to the rudder blade rotation actuator cylinder through a keyway hole, and the rudder blade rotation actuator cylinder is fixedly mounted on the base tooling 7 through a keyway hole. After the rocker mechanism 6 and the rotation transfer flange 4 are assembled, the force transmission rod on the rocker mechanism 6 is aligned with the initial position of the annular hole on the rotation transfer flange 4, that is, the initial angle is zeroed. The rotational force is provided by the forward and reverse rotation of the DC motor and the controller 1, and the rotational force is transmitted through the force transmission rod on the rocker mechanism 6, thereby realizing the horizontal transmission of the entire torque. It should be noted that after the entire automatic rotation system is assembled, it is necessary to ensure that the center rotation position is on a horizontal straight line, that is, to ensure the horizontality.

[0027] Referring to Figures 1 to 4, the measurement system includes an angle sensor 5 and a data collector. The angle sensor 5 is a contactless angle sensor. The dynamic torque sensor 3 collects the time domain signal of the torque output during the entire transmission process under dynamic action. When the internal structure of the rotary actuator is damaged or cracked, the torque will be too small. At this time, the output signal of the dynamic torque sensor 3 can be used for real-time monitoring. The dynamic torque sensor 3 and the angle sensor 5 are both connected to the data collector, and the signals of the dynamic torque sensor 3 and the angle sensor 5 are input into the data collector. The measurement system collects parameters, the angle of the main measuring mechanism during operation, the torque magnitude, and the number of operations through the data collector. The data collector obtains the changes in torque load during multiple actions while monitoring the angle in real time. The data collector, DC motor and controller 1 are all electrically connected to the control system. The control system adopts Siemens S7-200Smart-SR20 (CPUSR20). The DC motor and controller 1 are connected to the signal output end of Siemens S7-200Smart-SR20 (CPUSR20) to realize the forward and reverse functions. Siemens S7-200Smart-SR20 (CPUSR20) realizes the human-computer interaction control interface through Siemens Smart700IEV3.

[0028] 1 to 4 , the state holding release system enables the DC motor and controller 1 to maintain the rudder blade rotating actuator at a fixed angle after rotating to the fixed angle, and enables the rudder blade rotating actuator to return to the original position after maintaining the state for a certain period of time.

[0029] Referring to Figures 1 to 4, the state-holding release system includes an electromagnet mechanism 8, a fixed disc 9, an electromagnet sensing block 10, a stop pin 12, an initial proximity sensor 13, a terminal proximity sensor 14, and a proximity sensing pin 16. The proximity sensing pin 16 is threadedly connected to the rocker mechanism 6, and the stop pin 12, the initial proximity sensor 13, and the terminal proximity sensor 14 are fixedly mounted on the fixed disc 9 by screws and nuts. The fixed disc 9 is fixedly connected to the base fixture 7, and the two form an integrated structure. The electromagnet sensing block 10 is mounted on the rocker mechanism 6, and the electromagnet mechanism 8 includes an electromagnet 11; the electromagnet 11 is a key component for torque holding and torque release, and plays a key role in torque holding and torque release. The contact surface of the electromagnet 11 can be adjusted and adapted to fit the electromagnet sensing block 10. The electromagnet 11, stop latch 12, initial proximity sensor 13, termination proximity sensor 14, and proximity sensing latch 16 are all electrically connected to the control system. The initial proximity sensor 13 and termination proximity sensor 14 serve as signal sensors and are connected to the signal input terminal of Siemens S7-200Smart-SR20 (CPUSR20).

[0030] Referring to Figures 1 to 4, in the initial state, the stop pin 12 contacts the slot on the rocker mechanism 6 to prevent excessive angular movement. When the system is running, the proximity sensing pin 16 contacts the initial proximity sensor 13, which transmits a signal to the DC motor and controller 1, causing the DC motor and controller 1 to reverse. When the electromagnet sensing block 10 reaches the final rotation angle, the proximity sensing pin 16 contacts the final proximity sensor 14, causing the DC motor and controller 1 to stop. At the same time, the electromagnet 11 contacts the electromagnet sensing block 10 and is electrically attracted, achieving the rotation angle holding state. After the holding state ends, the electromagnet sensing block 10 loses power and releases the electromagnet sensing block 10. The force transmission rod on the rocker mechanism 6 performs a free release movement under no-load conditions through the annular hole on the rotation transmission flange 4, achieving the automatic return state of the rotation angle, which can fully simulate the state of the rudder blade rotary actuator being freely released.

[0031] Referring to Figures 1 to 4, specifically, the electromagnet 11 is fixed to the angle adjustment bracket fixture 15 by screws, and the angle adjustment bracket fixture 15 is assembled by a multi-link mechanism; the angle adjustment bracket fixture 15 can realize the adjustment of the front and back, up and down, left and right angles, and the contact surface angle of the electromagnet 11 is adjusted by the angle adjustment bracket fixture 15, thereby realizing that the contact surface of the electromagnet 11 can be adjusted and adapted to fit the electromagnet sensing block 10 on the rocker arm mechanism 6.

[0032] Referring to Figures 1 to 4, the automatic rotation system in this reliability assessment test mechanism provides rotational force through the forward and reverse rotation of the DC motor and controller 1, and then transmits the rotational force through the force transmission rod on the rocker mechanism 6. The measurement system collects parameters, the angle, torque size, and operation times of the main measurement mechanism during operation through a data collector. The control system mainly controls the forward and reverse rotation of the DC motor and controller 1 and the on and off time of the electromagnet 11, while the state holding and release system realizes the state holding and release of the rudder blade rotary actuator cylinder by turning the electromagnet 11 on and off. The above-mentioned method realizes the automatic expansion and closing action of the rudder blade rotary actuator cylinder under the actual working state of the simulation, and obtains the change relationship of the torque load degradation over time during multiple actions, providing data support for the reliability assessment of the rudder blade rotary actuator cylinder. Its structural design meets the requirements of loading and stress state, and can perform reliability assessment of the rotary actuator cylinder, which has great practical significance.

[0033] The above content is a further detailed description of the present invention in conjunction with specific preferred embodiments, and the specific implementation of the present invention should not be considered to be limited to these descriptions. For those skilled in the art of the present invention, several simple deductions or substitutions can be made without departing from the concept of the present invention, and the above structures should be considered to fall within the scope of protection of the present invention.

Claims

1. A test mechanism for evaluating the reliability of automatic rotation of a rudder blade rotary actuator, characterized by: Including automatic rotation system, state holding release system, measurement system and control system; The automatic rotation system provides rotational power and realizes power transmission. The automatic rotation system includes a DC motor and a controller (1), a dynamic torque sensor (3), a rocker mechanism (6) and a base tool (7). The DC motor and the controller (1) can realize forward and reverse rotation and speed regulation functions, and also have a deceleration and braking function. The DC motor and the controller (1) are connected to the dynamic torque sensor (3). The dynamic torque sensor (3) outputs torque to the force transmission rod on the rocker mechanism (6). The rocker mechanism (6) is directly connected to the rudder blade rotation actuator cylinder. The rudder blade rotation actuator cylinder is fixedly installed on the base tool (7). Rotational force is provided by the forward and reverse rotation of the DC motor and the controller (1), and then the rotational force is transmitted through the force transmission rod on the rocker mechanism (6), thereby realizing the horizontal transmission of the entire torque. The state holding release system enables the DC motor and the controller (1) to maintain the state of the rudder blade rotating actuator at this angle after rotating to a fixed angle, and enables the rudder blade rotating actuator to return to the original position after maintaining this state for a certain period of time; The measuring system comprises an angle sensor (5) and a data collector. The dynamic torque sensor (3) and the angle sensor (5) are both data-connected to the data collector. The data collector obtains changes in torque load during multiple movements while monitoring the angle in real time. The data collector, the DC motor and the controller (1) are all electrically connected to a control system.

2. The automatic rotation reliability evaluation test mechanism for a rudder blade rotary actuator according to claim 1, characterized in that: The state holding release system comprises an electromagnet mechanism (8), a fixed disc (9), an electromagnet sensing block (10), a stop latch (12), an initial proximity sensor (13), a termination proximity sensor (14), and a proximity sensing latch (16). The proximity sensing latch (16) is connected to the rocker mechanism (6). The stop latch (12), the initial proximity sensor (13), and the termination proximity sensor (14) are mounted on the fixed disc (9). The fixed disc (9) is connected to the base tooling (7). The electromagnet sensing block (10) is mounted on the rocker mechanism (6). The electromagnet mechanism (8) comprises an electromagnet (11). The electromagnet (11) is a key component for torque holding and torque release. The contact surface of the electromagnet (11) can be adjusted and adapted to fit the electromagnet sensing block (10). The electromagnet (11), the stop latch (12), the initial proximity sensor (13), the termination proximity sensor (14), and the proximity sensing latch (16) are all electrically connected to the control system. In the initial state, the stop pin (12) contacts the slot on the rocker mechanism (6) to prevent over-angle movement; when the system is running, the proximity sensing pin (16) contacts the initial proximity sensor (13), and the initial proximity sensor (13) transmits a signal to the DC motor and the controller (1), and the DC motor and the controller (1) move in the reverse direction. When the electromagnet sensing block (10) reaches the terminal state angle in rotation, the proximity sensing pin (16) contacts the terminal proximity sensor (14), and the DC motor and the controller (1) stop moving. At the same time, the electromagnet (11) contacts the electromagnet sensing block (10) and is electrically attracted. At this time, the rotation angle holding state can be achieved. After the holding is completed, the electromagnet sensing block (10) loses power and releases the electromagnet sensing block (10). The force transmission rod on the rocker mechanism (6) is made through the annular hole on the rotation transmission flange (4). The free release movement when there is no force loading can realize the automatic return state of the rotation angle, which can completely simulate the state of the rudder blade rotary actuator being freely released.

3. The automatic rotation reliability evaluation test mechanism for a rudder blade rotary actuator according to claim 2, characterized in that: The electromagnet (11) is fixed on an angle adjustment bracket fixture (15), and the angle of the contact surface of the electromagnet (11) is adjusted by the angle adjustment bracket fixture (15), thereby enabling the contact surface of the electromagnet (11) to be adjusted and adapted to fit the electromagnet sensing block (10) on the rocker arm mechanism (6).

4. The automatic rotation reliability evaluation test mechanism for a rudder blade rotary actuator according to claim 2, characterized in that: The torque output end of the dynamic torque sensor (3) is provided with a circular flange, the circular flange is connected to a rotation transmission flange (4), the rotation transmission flange (4) is connected to a force transmission rod on a rocker mechanism (6), the torque output end of the dynamic torque sensor (3) outputs torque, and the dynamic torque sensor (3) outputs the torque to the force transmission rod on the rocker mechanism (6) through an annular hole on the rotation transmission flange (4).

5. The automatic rotation reliability evaluation test mechanism for a rudder blade rotary actuator according to claim 4, characterized in that: The force transmission rod on the rocker mechanism (6) is aligned with the annular hole on the rotation transmission flange (4) at the initial position.

6. The automatic rotation reliability evaluation test mechanism for a rudder blade rotary actuator according to claim 1, characterized in that: The DC motor and controller (1) are connected to the torque input end of the dynamic torque sensor (3) via a coupling (2).

7. The automatic rotation reliability evaluation test mechanism for a rudder blade rotary actuator according to claim 1, characterized in that: The rocker mechanism (6) is directly connected to the rudder blade rotating actuator cylinder through a keyway hole, and the rudder blade rotating actuator cylinder is fixedly installed on the base tooling (7) through the keyway hole.

8. The automatic rotation reliability evaluation test mechanism for a rudder blade rotary actuator according to claim 1, characterized in that: The DC motor and controller (1) are fixedly mounted on a horizontal motor base through mounting holes.

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