Steering engine rudder wing testing tool

Abstract

A steering engine rudder wing testing tool comprises a base and a testing assembly. A supporting ring is arranged in the center of the top face of the base and used for containing a steering engine, and four limiting grooves evenly formed in the circumferential direction of the supporting ring at intervals are formed in the top face of the base. The testing assembly comprises four fixing seats and four bearing seats which are located in the limiting grooves and are adjustable in position, torsion bar springs which are detachably connected are arranged between the fixing seats and the bearing seats, two clamping plates are arranged on the sides, facing the supporting ring, of the bearing seats, and the clamping plates are connected to one ends of the torsion bar springs, rotate around the axes of the torsion bar springs and are used for clamping rudder wings. Fixing heads are arranged in the fixing seat and the bearing seat in a penetrating mode, the two ends of the torsion rod spring are connected into the fixing heads respectively, the end, facing the supporting ring, of the fixing head located in the bearing seat is connected with the coupler, one end of the coupler is connected with the installation block, the clamping plate is connected to the installation block, and an angle encoder is installed on the bearing seat. The tool can test the four-shaft four-rudder steering engine at one time, the efficiency is improved, and the torsion bar spring is convenient to adjust.

Description

TECHNICAL FIELD

[0001] The utility model relates to rudder technology field especially relates to a rudder rudder wing test tool. BACKGROUND

[0002] In the rudder test system, the domestic manufacturers mainly adopt the structure form of symmetrical four tension springs at present, and the elastic element is four tension springs with same parameters, in order to ensure that the same torque can be provided when the rudder wing is reversed, and no torque is outputted when the zero position, so that one upper and lower tension spring is installed on both sides of each shaft, the maximum stretching length is within the linear working range of the tension spring, and the minimum stretching length is still greater than the free length of the tension spring. 2 When the elastic coefficient of each tension spring is k, the middle pull rod is L, and the rotation angle is θ, the torque provided is L 2 ×k×tgθ, and when the rotation angle is small, the torque is approximately L 2 ×k×θ. The current technology is relatively simple in principle, and the cost is not high, but four tension springs are used for each shaft, the space is occupied more, and only two shafts can be tested at the same time, four shafts cannot be tested at the same time, the test efficiency is low when the rudder to be tested is four-axis four-rudder, in addition, the structure is complex due to four tension springs for each shaft, the adjustment of the tension spring is troublesome, and the angle and the output torque are linearly proportional only when the rotation angle is small, and the application range is small. CONTENT OF THE UTILITY MODEL

[0003] In view of the above-mentioned deficiencies of the related prior art, the application provides a rudder rudder wing test tool, which can test four-axis four-rudder rudders at one time, improve the efficiency, and the adjustment of the torsion bar spring is convenient, and has strong practicability.

[0004] In order to achieve the above-mentioned purpose, the utility model adopts the following technology:

[0005] A rudder rudder wing test tool, comprising: a base, a test assembly.

[0006] The center of the top surface of the base is provided with a support ring for placing the rudder, and the top surface of the base is provided with four limiting grooves arranged uniformly along the circumferential direction of the support ring; the test assembly comprises four fixing seats and four bearing seats respectively located in the limiting grooves and adjustable in position, and the bearing seat is located between the support ring and the fixing seat, the torsion bar spring is detachably connected between the fixing seat and the bearing seat, the side of the bearing seat facing the support ring is provided with two clamping plates, the clamping plates are connected to one end of the torsion bar spring, and are rotatably arranged around the axis, for clamping the rudder wing.

[0007] Further, the fixing head in the fixing base is locked by a screw, and the fixing head in the bearing base is rotationally arranged, and the two fixing heads are both provided with a plurality of clamping blocks arranged in the circumferential direction at the end facing each other, and the adjacent two clamping blocks are spaced apart, and the cross section of the clamping block is a sector, and the torsion bar spring is arranged at the inner side of the clamping block at both ends, and the outer side of the clamping block is provided with a first U-shaped clamp, and the outer side of the first U-shaped clamp is provided with a screw for locking the torsion bar spring.

[0008] Further, the clamping plate is connected to the mounting block, one end of the mounting block is connected to the shaft coupling, and the end of the fixing head in the bearing base facing the support ring is connected to the shaft coupling.

[0009] Further, the bearing base is provided with an angle encoder on the side away from the support ring, and the fixing head in the bearing base passes through the angle encoder and is coaxially arranged.

[0010] Further, the outer side of the clamping plate is provided with a second U-shaped clamp, and the outer side of the second U-shaped clamp is provided with a screw, and one end of the screw abuts the side surface of one of the clamping plates, for locking the rudder wing.

[0011] Further, the side surface of the support ring is provided with a plurality of screws in the circumferential direction for locking the steering gear, and the side surface of the support ring is provided with a positioning shaft for positioning the steering gear.

[0012] Further, a plurality of threaded holes are arranged in the length direction of the limiting groove, and a screw is arranged in the threaded hole for locking the fixing base and the bearing base.

[0013] The utility model has the advantages that: four circumferentially arranged torsion bar springs are arranged, the steering gear of four-axis four-rudder can be tested at one time, the efficiency is improved, compared with the plurality of springs used in the prior art, the structure is simpler, the influence of other components is smaller, the precision is further improved, and the torsion bar spring is more convenient and faster to adjust. BRIEF DESCRIPTION OF DRAWINGS

[0014] The drawings described herein are only for illustrating the selected embodiments, not all possible embodiments, and are not intended to limit the scope of the utility model.

[0015] Figure 1 It is a three-dimensional schematic view of the overall structure of the embodiment of the application.

[0016] Figure 2 It is a three-dimensional schematic view of the support ring of the embodiment of the application.

[0017] Figure 3 It is a three-dimensional schematic view of the fixing head mounted in the fixing base of the embodiment of the application.

[0018] Figure 4 This is a schematic diagram of the fixing head being installed in the bearing housing according to an embodiment of this application. Detailed Implementation

[0019] To make the objectives, technical solutions and advantages of the present utility model clearer, the implementation methods of the present utility model will be described in detail below with reference to the accompanying drawings. However, the embodiments described in the present utility model are only some embodiments of the present utility model, and not all embodiments.

[0020] like Figures 1-4 As shown, this example provides a servo rotor blade testing fixture, including: a base 100 and a testing component 200.

[0021] A support ring 101 is provided at the center of the top surface of the base 100 for placing the servo motor. The top surface of the base 100 is provided with four limiting grooves 102 evenly spaced along the circumference of the support ring 101. The test assembly 200 includes four fixed seats 201 and four bearing seats 202 located in the limiting grooves 102 and whose positions are adjustable. The bearing seats 202 are located between the support ring 101 and the fixed seats 201. A torsion bar spring 203 is provided between the fixed seats 201 and the bearing seats 202. One end of the torsion bar spring 203 in the fixed seat 201 is fixed, while the other end in the bearing seat 202 is rotatably set. Two clamping plates 204 are provided on the side of the bearing seat 202 facing the support ring 101. Each clamping plate 204 is connected to one end of the torsion bar spring 203 and is rotatably set around its axis for clamping the servo wing.

[0022] Specifically, both the fixed base 201 and the bearing housing 202 are provided with fixed heads 205. The fixed head 205 in the fixed base 201 is locked with screws, and the fixed head 205 in the bearing housing 202 is rotatably mounted. At the opposite ends of the two fixed heads 205, multiple spaced clamping blocks 206 are provided along the circumferential direction. There is a gap between adjacent clamping blocks 206. The clamping block 206 has a fan-shaped cross-section with an arc-shaped central end. The two ends of the torsion bar spring 203 are respectively inserted inside the clamping block 206. A first U-shaped clamp 207 is provided on the outer side of the clamping block 206. 7. Screws are provided on the outside to lock the torsion bar spring 203. During use, the two ends of the torsion bar spring 203 are respectively inserted between the clamps 206 of the two fixing heads 205, and locked together with the first U-shaped clamp 207. Since there is a gap between the clamps 206 and the center end is arc-shaped, it can accommodate torsion bar springs 203 of different diameters. At the same time, the internal through-type setting of the fixing head 205 can also make a small adjustment to the length of the torsion bar spring 203 between the fixing seat 201 and the bearing seat 202 to meet the requirements of different elastic coefficients.

[0023] During the test, the torsion bar spring 203 as a kind of elastic element is a torsion bar made of spring steel, the cross section of the torsion bar is usually circular, a few are pipe type and rectangular, and the cross section of the torsion bar spring 203 in the application adopts circular shape;When a torsion T is applied to one end of the torsion bar spring, the torsion bar spring itself will be twisted and deformed around the spring axis, and when the spring is deformed into elastic deformation, the torsion angle φ is as follows:

[0024]

[0025] Wherein: φ, torsion angle (°) of the torsion bar spring;T, applied torque (Nmm);L, acting length (mm) of the torsion bar spring;G, tangent modulus (MPa) of the material;D, outer diameter (mm) of the torsion bar spring;It can be seen that when L, G and d are constant, the torsion angle φ and the applied torque are in linear proportional relationship, that is, the rudder wing rotation angle and the hinge moment applied to the rudder wing are in linear proportional relationship, so as to realize the test of the rudder wing of the rudder.

[0026] Specifically, the clamping plates 204 are connected to the mounting block 208, one end of the mounting block 208 is connected to the shaft coupling 209, the fixed head 205 in the bearing seat 202 is connected to the shaft coupling 209 at the end facing the support ring 101, and the rotating torque of the clamping plate 204 is transmitted to the torsion bar spring 203 through the shaft coupling 209, so that the torsion bar spring 203 is deflected.

[0027] Specifically, the angle encoder 211 is installed on the side of the bearing seat 202 away from the support ring 101, the fixed head 205 in the bearing seat 202 penetrates through the angle encoder 211 and is coaxially arranged, when the rudder drives the rudder wing to rotate, the torsion bar spring 203 is rotated by the clamping plate 204 to a corresponding angle, so that a corresponding torque is added to the rudder wing, and the angle encoder 211 feeds back the rotation angle of the rudder wing to the test system, so as to test the dynamic characteristics of the rudder.

[0028] Specifically, the second U-shaped clamp 210 is arranged on the outer side of the clamping plate 204, the second U-shaped clamp 210 is provided with a screw outside, one end of the screw abuts against the side surface of one of the clamping plates 204, and the screw is used for locking the rudder wing and ensuring that the rotating torque is smoothly transmitted when the rudder wing rotates.

[0029] Specifically, a plurality of screws are arranged on the side surface of the support ring 101 in the circumferential direction, which are used for locking the rudder, and the support ring 101 is provided with the positioning shaft 104 on the side surface, which is used for positioning the rudder, so that the position of the rudder is stable, and the test result is not affected by the shaking of the rudder during the test.

[0030] Specifically, the limiting groove 102 is provided with a plurality of threaded holes 103 along the length direction thereof, and screws are arranged in the threaded holes 103, so as to lock the fixing seat 201 and the bearing seat 202, thereby facilitating the adjustment of the positions of the fixing seat 201 and the bearing seat 202, and meeting the requirements of torsion bar springs 203 with different lengths.

[0031] Since the above is only the preferred embodiment of the present application, and is not used to limit the present application, it is obvious that those skilled in the art can make various modifications and changes to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and changes of the present application belong to the scope of the claims of the present application and the equivalent technologies, the present application also intends to include these modifications and changes.

Claims

1. A rudder blade test tool for a rudder, characterized in that, The utility model relates to a rudder wing test device, including: The base (100) top center is equipped with the support ring (101) for placing the rudder, and the base (100) top is equipped with four limit slot (102) evenly arranged along the circumferential direction of the support ring (101); Test component (200), including four fixed seat (201) and four bearing seat (202) in the limit slot (102) respectively and the position adjustable, and the bearing seat (202) is located between the support ring (101) and the fixed seat (201), and the fixed seat (201) is equipped with the detachable connection torsion bar spring (203) between the bearing seat (202), the one side of bearing seat (202) towards the support ring (101) is equipped with two clamping plate (204), the clamping plate (204) is all connected to one end of torsion bar spring (203), and is rotatably arranged around its axis, is used for clamping rudder wing.

2. The steering gear test fixture of claim 1, wherein, The fixed seat (201) and the bearing seat (202) are all equipped with fixed head (205), and the fixed head (205) in the fixed seat (201) is locked with screw, the fixed head (205) in the bearing seat (202) is rotatably arranged, and the end of the two fixed head (205) opposite to each other is equipped with a plurality of interval clamping blocks (206) along the circumferential direction, the adjacent two clamping blocks (206) have interval, and the clamping block (206) cross section is sector, the inner side of the clamping block (206) is equipped with the torsion bar spring (203) two ends respectively, and the outer side of the clamping block (206) is equipped with first U-shaped clamp (207), the outer side of first U-shaped clamp (207) is equipped with screw, is used for locking the torsion bar spring (203).

3. The steering gear test fixture of claim 2, wherein, The clamping plate (204) is all connected on the mounting block (208), one end of the mounting block (208) is connected on the shaft coupling (209), and the end of the fixed head (205) in the bearing seat (202) towards the support ring (101) is connected with the shaft coupling (209).

4. The test fixture of claim 2, wherein, The side away from the support ring (101) of the bearing seat (202) is installed with angle encoder (211), and the fixed head (205) in the bearing seat (202) passes through the angle encoder (211) and is coaxially arranged.

5. The steering gear test fixture of claim 1, wherein, The outer side of the clamping plate (204) is equipped with second U-shaped clamp (210), the outer side of second U-shaped clamp (210) is equipped with screw, and one end of the screw is abutted to the side surface of one of the clamping plate (204), is used for locking rudder wing.

6. The steering gear test fixture of claim 1, wherein, The side of the support ring (101) is equipped with a plurality of screws along the circumferential direction, is used for locking the rudder, and the side of the support ring (101) is equipped with positioning shaft (104), is used for positioning the rudder.

7. The steering gear test fixture of claim 1, wherein, A plurality of thread holes (103) are arranged in the limit slot (102) along the length direction, and screws are arranged in the thread holes (103) to lock the fixed seat (201) and the bearing seat (202).

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