A composite steering gear gas rudder blade drilling device

Abstract

The present invention discloses a composite servo gas rudder blade drilling device, and relates to the composite servo assembly technical field. The composite servo gas rudder blade drilling device disclosed by the present invention comprises a base, a push plate, a positioning sleeve and a slider, etc. Slider grooves are arranged between the four bosses on the base, a core shaft is fixed on the center hole of the base by a set screw, an adjustment piece is arranged at the position of the core shaft corresponding to the slider groove, a slider is installed in the slider groove, the slider is connected to the adjustment piece, a pressure plate is arranged on the top surface of the slider, and the pressure plate is fixed on the boss. The composite servo gas rudder blade drilling device and its operation method provided by the present invention ensure that the center planes of the two corresponding gas rudder blades are in the same plane, and the angle between the center plane of the composite servo and the center plane shall not be greater than 0.05 degrees, can meet the technical requirements of various aircraft gas rudder blade drilling, are easy to operate, reduce the operating skill requirements for workers, and improve the production efficiency of the product.

Description

Technical Field

[0001] The present invention belongs to the technical field of composite servo assembly, and in particular relates to a drilling device and an operating method for gas rudder blades of composite servos of various aircraft, which can be widely used in the assembly and production of gas rudder blades of composite servos of aircraft. Background Art

[0002] When the compound servo gas rudder blades are assembled in the general assembly workshop, the design requires that the four gas rudder blades of the compound servo have very high dimensional accuracy requirements with respect to the center line of the compound servo. At the same time, there are also symmetry requirements for the center line of the compound servo for the two corresponding gas rudder blades, and the center planes of the two corresponding gas rudder blades are in the same plane, and the angle between them and the center plane of the compound servo shall not be greater than 0.05 degrees.

[0003] In the past production, the solution adopted was: after the composite servo was installed on the base, the four gas rudder blades were pressed toward the base with a push plate under the action of the positioning sleeve and the tightening parts. Due to the manufacturing error factor of the V-shaped surface of the gas rudder blade, the centerline dimension accuracy of the four gas rudder blades to the composite servo and the symmetry requirements of the two corresponding gas rudder blades to the centerline of the composite servo could not be guaranteed. This requires the operator to measure the centerline dimensions of the four gas rudder blades to the composite servo and the symmetry dimensions of the two corresponding gas rudder blades to the centerline of the composite servo after installing the gas rudder blades, and then according to the measurement results, the contact surface of the gas rudder blade and the base (such as Figure 1 Add thin copper sheets to adjust the size to meet the requirements of the gas rudder blade for the centerline size and symmetry of the composite servo (see Figure 1 ). This requires high skills of the operators and the operation process is complicated. At the same time, due to the addition of thin copper sheets, the V-shaped surface of the gas rudder blade is out of contact with the V-shaped surface of the base, so that it is impossible to ensure that the center planes of the two corresponding gas rudder blades are in the same plane and the angle between them and the center plane of the composite servo is not greater than 0.05 degrees. Summary of the invention

[0004] The object of the present invention is to provide a composite servo gas rudder blade drilling device and an operating method, which can not only ensure the symmetry requirement of two corresponding gas rudder blades with respect to the center line of the composite servo, but also ensure that the center planes of the two corresponding gas rudder blades are in the same plane and the angle between the center plane of the composite servo and the center plane shall not be greater than 0.05 degrees, so as to meet the assembly production requirements of the composite servo gas rudder blades.

[0005] In order to solve the above technical problems, the present invention provides a composite steering gear gas rudder blade drilling device, comprising a base, a push plate and a positioning sleeve, the push plate is arranged on the composite steering gear, the gas rudder blade is pushed close to the base by a tightening member arranged on the positioning sleeve, four bosses are arranged on the base, slider grooves are arranged between the four bosses, a core shaft is fixed to the center hole of the base by a set screw, an adjusting member is arranged at the position of the core shaft corresponding to the slider groove, a slider is installed in the slider groove, the slider is connected to the adjusting member, a pressure plate is arranged on the top surface of the slider, and the pressure plate is fixed on the boss.

[0006] Furthermore, a convex groove is provided at one end of the slider, a groove is provided at the other end of the slider, the bayonet of the adjustment member is snapped into the convex groove, and a V-shaped groove is provided in the slider.

[0007] Furthermore, eight pressure plates are provided, and the pressure plates are provided on both sides of the top surface of the boss, and one side of the pressure plate is provided on the top surface of the slider.

[0008] Furthermore, the adjusting member is configured as an adjusting screw, and a bolt of the adjusting screw is screwed into a screw hole of the core shaft.

[0009] Furthermore, a composite servo is installed on the base, the composite servo is installed on the positioning sleeve, four groups of push plates are arranged inside the positioning sleeve, the push plates are movable relative to the positioning sleeve through a tightening member, and the four groups of push plates are respectively arranged on the outside of the four slider grooves.

[0010] Furthermore, the tightening member is configured as a tightening screw.

[0011] Furthermore, positioning blocks are arranged on both sides of the boss facing the push plate, and two groups of positioning blocks on adjacent bosses form a positioning surface.

[0012] Furthermore, a potentiometer seat is installed on the support plate of the composite steering gear.

[0013] The present invention also provides an operation method of a composite steering engine gas rudder blade drilling device, which specifically comprises the following steps:

[0014] S1. First, adjust the length of the four adjustment screws on the mandrel so that the slider 4 moves to the innermost position in the corresponding slider groove of the base;

[0015] S2. Install the composite servo onto the base. The grooves on the four rotating shafts of the composite servo must be snapped into the four clamping blocks of the base. Install the potentiometer holder onto the support plate of the composite servo.

[0016] S3. Fix the positioning sleeve on the composite servo, then place the four push plates on the corresponding positions outside the slider groove inside the positioning sleeve, tighten the screws to push the push plates so that the gas rudder blades are against the positioning surface of the base boss, do not press tightly, and make the two corresponding gas rudder blades symmetrical to the central axis of the composite servo;

[0017] S4. Turn the adjusting screw to push the slider until the V-shaped groove on the slider is in close contact with the V-shaped surface of the gas rudder blade, ensuring that the center planes of the two corresponding gas rudder blades are in the same plane and the angle between them and the center plane of the compound servo is not greater than 0.05 degrees.

[0018] The present invention has achieved the following beneficial effects:

[0019] The present invention meets the coaxiality requirement by matching the center truncated cone of the base with the center circular hole of the composite steering gear; the four machined positioning surfaces of the base are in contact with the gas rudder blade surface to ensure the dimensional accuracy of the gas rudder blade to the center line of the composite steering gear and the symmetry requirement of the two corresponding gas rudder blades to the center line of the composite steering gear; a slider is arranged in the slider groove, and the V-shaped surface on the slider is in contact with the V-shaped surface of the gas rudder blade through the movement of the slider, ensuring that the center planes of the two corresponding gas rudder blades are in the same plane, and the angle between the center plane of the composite steering gear and the center plane is not greater than 0.05 degrees. In this way, the assembly production requirements of the composite steering gear gas rudder blade are met.

[0020] The arrangement of the push plate and the positioning sleeve of the present invention facilitates the movement of the gas rudder blade so that the gas rudder blade contacts the machined positioning surfaces of the base 4; the arrangement of the adjusting member facilitates the movement of the slider so that the V-shaped groove of the slider contacts the V-shaped surface of the gas rudder blade closely; the arrangement of the pressure plate prevents the slider from escaping from the base; the entire gas rudder blade drilling device and operation method provided by the present invention can meet the technical requirements of gas rudder blade drilling for various aircrafts, is easy and convenient to operate, reduces the requirements on the operating skills of workers, and improves the production efficiency of the product. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of an existing composite steering engine gas rudder blade drilling device;

[0022] Figure 2 is a top view of a drill matching device according to an embodiment of the present invention;

[0023] Figure 3 This is a front view of a drill assembly device according to an embodiment of the present invention;

[0024] Figure 4 It is a structural schematic diagram of a drilling device according to an embodiment of the present invention;

[0025] Figure 5 is a schematic structural diagram of a base according to an embodiment of the present invention;

[0026] Figure 6Schematic diagram of the structure of a slider according to an embodiment of the present invention.

[0027] The accompanying drawings are marked with the following symbols: 1. base; 2. push plate; 3. positioning sleeve; 4. slider; 5. pressure plate; 6. spindle; 7. potentiometer seat; 8. adjustment screw; 9. screw one; 10. screw two; 11. tightening screw; 12. set screw; 13. screw three; 14. gas rudder blade; 15. compound servo; 101. boss; 102. slider groove; 103. positioning block; 104. clamping block; 401. convex groove; 402. V-shaped groove; 403. groove. DETAILED DESCRIPTION

[0028] For example, certain words are used in the specification and claims to refer to specific components. Those skilled in the art should understand that hardware manufacturers may use different terms to refer to the same component. This specification and claims do not use differences in names as a way to distinguish components, but use differences in the functions of components as the criteria for distinction. The subsequent description of the specification is a preferred embodiment of the present application, but the description is for the purpose of illustrating the general principles of the present application and is not intended to limit the scope of the present application. The scope of protection of the present application shall be determined by the attached claims.

[0029] The present application is further described in detail below in conjunction with the accompanying drawings, but is not intended to limit the present application. Specific embodiment:

[0031] like Figure 2-4 As shown, a composite steering engine gas rudder blade drilling device according to an embodiment of the present invention comprises a base 1, a push plate 2 and a positioning sleeve 3. A composite steering engine 15 is mounted on the base 1, and the composite steering engine 15 is fixed with the positioning sleeve 3 by screws 13. Four groups of push plates 2 are arranged inside the positioning sleeve 3, one end of the push plate 2 abuts against the tightening screw 11 threadedly connected to the positioning sleeve 3, and the other end of the push plate 2 contacts the gas rudder blade 14. The four groups of push plates 2 are respectively arranged on the outside of four slider grooves 102. A potentiometer seat 7 is arranged inside the push plate 2, and the potentiometer seat 7 is mounted on the support plate of the composite steering engine 15.

[0032] like Figure 2 , Figure 4 and Figure 5 As shown, four bosses 101 are provided on the base 1, and slider grooves 102 are provided between the four bosses 101. There are four slider grooves 102 in total for assembling the slider 4. A core shaft 6 is fixed to the center hole of the base 1 by a set screw 12, and an adjustment screw 8 is provided at the position of the core shaft 6 adjacent to the slider groove 102. The bolts of the four adjustment screws 8 are screwed into the corresponding screw holes of the core shaft 6.

[0033] like Figure 2 , Figure 4 and Figure 6As shown, the four slider grooves 102 are all equipped with sliders 4, one end of the slider 4 is provided with a convex groove 401, and the other end of the slider 4 is provided with a groove 403. The bayonet of the adjusting screw 8 is engaged in the convex groove 401, so that when the adjusting screw 8 is turned, the slider 4 can be driven to move forward and backward in the slider groove 102, which is convenient for operation. The slider 4 is provided with a V-shaped groove 402. When the adjusting screw 8 is turned to push the slider 4 until the V-shaped groove 402 of the slider 4 is in close contact with the V-shaped surface of the gas rudder blade 14, the V-shaped surface of the gas rudder blade 14 is inserted into the V-shaped groove 402, that is, when the center planes of the V-shaped grooves 402 of the two corresponding sliders 4 are in the same plane (the slider 4 is fixedly arranged in the slider groove 102), it can be ensured that the center planes of the two corresponding gas rudder blades 14 are in the same plane, and the angle between the center plane of the compound servo 15 and the center plane is not greater than 0.05 degrees.

[0034] like Figure 2 and Figure 4 As shown, pressure plates 5 are provided on both sides of the top surfaces of the four bosses 101, so a total of eight pressure plates 5 are provided. The eight pressure plates 5 are fixed to both sides of the top surfaces of the corresponding bosses 101 by screws 9, so that one side of the pressure plate 5 is placed on the top surface of the slider 4, that is, one side of two pressure plates 5 is used to fix the slider 4 in the slider groove 102 to prevent the slider 4 from escaping from the slider groove 102.

[0035] like Figure 4 and Figure 5 As shown, positioning blocks 103 are provided on both sides of the four bosses 101 facing the push plate 2, and the two groups of positioning blocks 103 on adjacent bosses 101 constitute a positioning surface. When the screws 11 are tightened to push the four push plates 2, the gas rudder blades 14 are pressed against the four positioning surfaces, ensuring the center line size accuracy requirements of the four gas rudder blades 14 to the composite servo 15 and the symmetry requirements of the center line of the two corresponding gas rudder blades 14 to the composite servo 15.

[0036] The operation method of the composite steering gear gas rudder blade drilling device of the present invention is as follows:

[0037] First, adjust the screwing length of the four adjustment screws 8 on the core shaft 6 so that the slider 4 moves to the innermost position in the corresponding slider groove 102 of the base 1. Install the compound servo 15 on the base 1, requiring the grooves on the four rotating shafts on the compound servo 15 to be clamped on the four clamping blocks 104 of the base 1, and install the potentiometer seat 7 on the support plate of the compound servo 15. Use screw three 13 to fix the positioning sleeve 3 on the compound servo 15, place the four push plates 2 in the corresponding positions of the device, tighten the screws 11 to push the push plates 2 so that the gas servo blade 14 rests on the positioning surface of the boss 101 of the base 1, and do not press it tightly, to ensure the dimensional accuracy requirements of the four gas servo blades 14 to the center line of the compound servo 15 and the symmetry requirements of the two corresponding gas servo blades 14 to the center line of the compound servo 15. Then, the adjusting screw 8 is turned to push the slider 4 until the V-shaped groove 402 on the slider 4 is in close contact with the V-shaped surface of the gas rudder blade 14, thereby ensuring that the center planes of the two corresponding gas rudder blades 14 are in the same plane and the angle between them and the center plane of the compound servo 15 shall not be greater than 0.05 degrees.

[0038] The composite steering engine gas rudder blade drilling device and operation method provided by the present invention only require the operator to install the composite steering engine 15 on the base 1, and use four M5 screws to push four push plates 2 to make four gas rudder blades 14 lean against the base 1. Since the four contact surfaces on the base 1 have guaranteed centerline size and symmetry accuracy during manufacturing, the centerline size accuracy of the four gas rudder blades 14 to the composite steering engine 15 and the symmetry requirements of the two corresponding gas rudder blades 14 to the centerline of the composite steering engine 15 are guaranteed. Then, the four sliders 4 in the base 1 are pushed to move by adjusting the four adjustment screws 8 until the V-shaped grooves 402 on the sliders 4 are in close contact with the V-shaped surfaces of the gas rudder blades 14, thereby ensuring that the center planes of the two corresponding gas rudder blades 14 are in one plane, and the angle between the center plane of the composite steering engine 15 and the center plane is not greater than 0.05 degrees.

[0039] It is worth noting that the machining accuracy requirements of the four positioning surfaces on the base 1 of the present invention should be able to meet the center line dimensional accuracy requirements of the composite servo 15 when the gas rudder blade 14 leans against the positioning surface and the symmetry requirements of the center line of the composite servo 15 between the two corresponding gas rudder blades 14.

[0040] Furthermore, the adjusting member and tightening member provided in the present invention are not limited to the adjusting screw 8 and the tightening screw 11, but also include other parts that can be used for adjustment or tightening.

[0041] The above description shows and describes several preferred embodiments of the present application, but as mentioned above, it should be understood that the present application is not limited to the form disclosed herein, and should not be regarded as excluding other embodiments, but can be used in various other combinations, modifications and environments, and can be modified within the scope of the application concept described herein through the above teachings or the technology or knowledge of the relevant field. The changes and modifications made by those skilled in the art do not depart from the spirit and scope of the present application, and should be protected by the claims attached to the present application.

Claims

1. A composite steering engine gas rudder blade drilling device, comprising a base (1), a push plate (2) and a positioning sleeve (3), wherein the push plate (2) is arranged on the composite steering engine (15), and the push plate (2) pushes the gas rudder blade (14) close to the base (1) through a tightening member arranged on the positioning sleeve (3), characterized in that: The base (1) is provided with four bosses (101), and slider grooves (102) are provided between the four bosses (101). A core shaft (6) is fixed to the center hole of the base (1) via a set screw (12), and an adjustment member is provided at the position of the core shaft (6) corresponding to the slider groove (102). A slider (4) is installed in the slider groove (102), and the slider (4) is connected to the adjustment member. A pressure plate (5) is provided on the top surface of the slider (4), and the pressure plate (5) is fixed to the boss (101); A convex groove (401) is provided at one end of the slider (4), a groove (403) is provided at the other end of the slider (4), the bayonet of the adjustment member is snap-fitted into the convex groove (401), and a V-shaped groove (402) is provided in the slider (4); A composite steering gear (15) is mounted on the base (1), a positioning sleeve (3) is fixed on the composite steering gear (15), four groups of push plates (2) are arranged inside the positioning sleeve (3), the push plates (2) are movable relative to the positioning sleeve (3) via a tightening member, and the four groups of push plates (2) are respectively arranged on the outside of four slider grooves (102).

2. The composite steering engine gas rudder blade drilling device according to claim 1, characterized in that: Eight pressing plates (5) are provided, and the pressing plates (5) are provided on both sides of the top surface of the boss (101), and one side of the pressing plate (5) is provided on the top surface of the slider (4).

3. The drilling device for composite steering engine gas rudder blade according to claim 1, characterized in that: The adjusting member is configured as an adjusting screw (8), and a bolt of the adjusting screw (8) is screwed into a screw hole of the core shaft (6).

4. The composite steering engine gas rudder blade drilling device according to claim 1, characterized in that: The tightening member is configured as a tightening screw (11).

5. The drilling device for composite steering engine gas rudder blade according to claim 4, characterized in that: Positioning blocks (103) are provided on both sides of the boss (101) facing the push plate (2), and two groups of positioning blocks (103) on adjacent bosses (101) form a positioning surface.

6. The drilling device for composite steering engine gas rudder blade according to claim 5, characterized in that: A potentiometer seat (7) is mounted on the support plate of the composite steering gear (15).

7. An operating method of the composite steering engine gas rudder blade drilling device according to any one of claims 1 to 6, characterized in that: The following steps are involved: S1. First, adjust the length of the four adjustment screws on the mandrel (6) so that the slider (4) moves to the innermost position in the corresponding slider groove (102) of the base (1); S2. Install the composite servo (15) on the base (1), requiring the grooves on the four rotating shafts of the composite servo (15) to be clamped on the four clamping blocks (104) of the base (1), and installing the potentiometer seat (7) on the support plate of the composite servo (15); S3. Fix the positioning sleeve (3) on the composite servo (15), then place the four push plates (2) at the corresponding positions outside the slider groove (102) inside the positioning sleeve (3), tighten the screws to push the push plates (2) so that the gas servo blade (14) rests on the positioning surface of the boss (101) of the base (1), without pressing tightly, so that the two corresponding gas servo blades (14) are symmetrical with respect to the central axis of the composite servo (15); S4. Turn the adjusting screw to push the slider (4) until the V-shaped groove (402) on the slider (4) is in close contact with the V-shaped surface of the gas rudder blade (14), ensuring that the center planes of the two corresponding gas rudder blades (14) are in the same plane and the angle between the center plane of the compound servo (15) and the center plane is not greater than 0.05 degrees.

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