A centering jig

Abstract

The utility model discloses a center positioning frame, including center frame body and embrace hoop device, the inside of center frame body is equipped with the positioning cavity of circular through, embrace hoop device fixed mounting is in the tail of rocket engine, embrace hoop device is in the positioning cavity and is loaded, a plurality of radial limit device is installed on center frame body, a plurality of radial limit device is evenly distributed along the circumference of positioning cavity, and radial limit device includes the limit gyro wheel of rotation installation, and limit gyro wheel touches the outer wall of embrace hoop device, the utility model discloses a embrace hoop device to embrace the tail of rocket engine, and the tail of rocket engine is loaded in the positioning cavity of center frame body, and the radial limit device of multiple radial limit device circumferentially installed in the positioning cavity is limited to carry out, so that the radial swing problem of the tail of rocket engine is better solved, the utility model only carries out radial positioning, does not influence the axial movement of rocket engine, and the normal performance of thrust test has no influence, the utility model has the advantages of reasonable design layout, and practical effect is good.

Description

Technical Field

[0001] This utility model relates to the technical field of thrust testing equipment, and more specifically, to a central positioning frame. Background Technology

[0002] In rocket engine thrust testing, after the rocket engine ignites, the position of its tail nozzle will inevitably oscillate radially. The radial oscillation of the tail nozzle not only affects the accurate acquisition of rocket engine thrust data, but also poses a risk to test safety. Therefore, solving the problem of radial oscillation at the tail of the rocket engine is an important issue in the development of rocket engine thrust testing equipment, and this case arises from this. Utility Model Content

[0003] The purpose of this invention is to address the needs of the prior art by providing a central positioning frame. This invention uses a clamping device to hold the tail of a rocket engine, which is then installed in the positioning cavity of the central frame. Multiple radial limiting devices installed circumferentially within the positioning cavity provide limiting, thus effectively solving the problem of radial swaying of the rocket engine tail.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] A central positioning frame includes a central frame body and a clamping device. The central frame body has a circular through-hole positioning cavity. The clamping device is fixedly installed at the tail of a rocket engine and is inserted into the positioning cavity. A plurality of radial limiting devices are installed on the central frame body. The plurality of radial limiting devices are evenly distributed along the circumference of the positioning cavity. Each radial limiting device includes a rotatably mounted limiting roller, and the limiting roller abuts against the outer wall of the clamping device.

[0006] Furthermore, the central frame includes an upper support frame and a lower support frame, which are stacked and connected to form a positioning cavity.

[0007] Furthermore, the clamping device includes an upper semicircle and a lower semicircle, which are fixedly connected by bolts. Two rings of reinforcing ribs are vertically welded to the outer walls of the upper and lower semicircles, and the two rings of reinforcing ribs are respectively located at both ends of the upper and lower semicircles in the width direction.

[0008] Furthermore, the radial limiting device is installed in a quantity of four, and the outer wall of the clamp device is provided with several notch areas, each notch area corresponding to a radial limiting device.

[0009] Furthermore, the radial limiting device also includes a telescopic mechanism, which is installed through the central frame, and the limiting roller is rotatably connected to the telescopic mechanism.

[0010] Furthermore, the telescopic mechanism includes a cylinder, a screw shaft, and a telescopic shaft. The cylinder is installed through and fixedly mounted on the central frame. The screw shaft is rotatably connected to the cylinder, with a portion of the screw shaft inserted into the cylinder. The inserted end of the screw shaft has a threaded section. The telescopic shaft is inserted into the cylinder and threadedly connected to the threaded section of the screw shaft. A guide groove is provided on the outer wall of the telescopic shaft. A guide screw is threadedly installed on the outer wall of the cylinder, with the end of the guide screw extending into the guide groove. A limit roller is rotatably mounted on the outer end of the telescopic shaft of the cylinder. A screw head is provided on the outer end of the screw shaft of the cylinder.

[0011] Furthermore, the two radial limiting devices installed on the upper support frame have handwheels fixedly connected to the screw shafts of their screw heads. The lower support frame has two manual operation holes, which are respectively set to correspond to the two radial limiting devices installed on the lower support frame. The screw shafts of the two radial limiting devices extend into the manual operation holes.

[0012] Furthermore, the top of the upper support frame is fixedly connected to two symmetrically arranged lifting lugs.

[0013] Furthermore, the lower support frame is provided with two symmetrically arranged legs, and the bottom of the legs is connected to a flange base plate.

[0014] The beneficial effects of this utility model are:

[0015] This invention uses a clamping device to hold the tail section of a rocket engine. The tail section is installed in the positioning cavity of the central frame, and multiple radial limiting devices installed circumferentially within the positioning cavity provide limiting, thus effectively solving the problem of radial sway of the rocket engine tail section. This invention only performs radial positioning and does not affect the axial movement of the rocket engine, so it has no impact on the normal conduct of thrust testing. This invention has the advantages of reasonable design layout, good practical effect, and convenient operation of the radial limiting device. Attached Figure Description

[0016] Figure 1 This is a three-dimensional structural diagram of a central positioning frame in this embodiment;

[0017] Figure 2 This is a front view schematic diagram of a central positioning frame in this embodiment;

[0018] Figure 3 for Figure 1 Enlarged view of point A in the image;

[0019] Figure 4 for Figure 2 Enlarged view at point B in the image;

[0020] Figure 5 for Figure 2 A magnified view of point C in the image.

[0021] Reference numerals: central frame 1, upper support frame 11, lifting lug 111, lower support frame 12, hand operation hole 121, support leg 122, flange base plate 123, positioning cavity 2, clamping device 3, upper semicircle 31, lower semicircle 32, reinforcing rib plate 33, notch area 34, radial limiting device 4, telescopic mechanism 41, cylinder 411, screw shaft 412, threaded section 4121, screw head 4122, telescopic shaft 413, guide groove 4131, guide screw 414, limiting roller 42, handwheel 43. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] like Figures 1-5The illustrated central positioning frame includes a central frame body 1 and a clamping device 3. For ease of manufacturing, the central frame body 1 is designed to include an upper support frame 11 and a lower support frame 12 (separate manufacturing is more convenient). The upper support frame 11 and the lower support frame 12 are stacked vertically and connected by flange bolts. The stacked connection of the upper support frame 11 and the lower support frame 12 forms a positioning cavity 2, which is circular and extends longitudinally (i.e., axially, in the thrust direction). The clamping device 3 is fixedly installed at the tail of the rocket engine. The clamping device 3 is designed for ease of use. The fabrication and installation also include an upper semicircular body 31 and a lower semicircular body 32, which are fixedly connected by bolts. After the bolt connection, the clamping device 3 is tightly fixed to the tail of the rocket engine. The radial oscillation of the tail of the rocket engine can generate the radial oscillation of the clamping device 3. Therefore, as long as the clamping device 3 is restricted, the radial oscillation of the tail of the rocket engine can be restricted. Before the thrust test, the clamping device 3 is pushed into the positioning cavity 2 (the diameter of the positioning cavity 2 is larger than the outer diameter of the clamping device 3). This utility model is based on the central frame 1. Several radial limiting devices 4 are installed. For optimal selection (considering cost and operational difficulty), the number of radial limiting devices 4 is set to four, which are evenly distributed around the circumference of the positioning cavity 2 (two on the upper support frame 11 and two on the lower support frame 12). Each radial limiting device 4 includes a telescopic mechanism 41 and a limiting roller 42. The telescopic mechanism 41 is installed through the central frame 1, and the limiting roller 42 is rotatably connected to the telescopic mechanism 41. The limiting roller 42 is installed facing inward towards the positioning cavity 2, and the telescopic mechanism 41 drives the limiting roller 42. Before the thrust test begins, all the limiting rollers 42 must contact the outer wall of the clamping device 3 to form a radial positioning of the clamping device 3 and the tail of the rocket engine. At the start of the thrust test, the swaying of the tail of the rocket engine is well suppressed due to the radial positioning, which makes the data on the thrust of the rocket engine more accurate and ensures the safety of the thrust test. In this utility model, each radial limiting device 4 needs to be designed to bear a lateral (radial) force of not less than 15% of the rated thrust.

[0024] like Figure 1 and Figure 3As shown, two rings of reinforcing ribs 33 are vertically welded to the outer walls of the upper semicircle 31 and the lower semicircle 32. The two rings of reinforcing ribs 33 are respectively located at both ends of the upper semicircle 31 and the lower semicircle 32 in the width direction. The reinforcing ribs 33 can enhance the rigidity of the upper semicircle 31 and the lower semicircle 32. Several notch areas 34 are provided on the outer wall of the clamping device 3. The notch areas 34 are corresponding to the radial limiting devices 4. The notch areas 34 are the contact positions of the limiting rollers 42. The notch areas 34 only need to be opened through the front and rear ends of the reinforcing ribs 33, without damaging the body of the upper semicircle 31 and the lower semicircle 32. In this utility model, the limiting rollers 42 can rotate in the front and rear directions (that is, the axial direction, the thrust direction). This design makes the limiting rollers 42 only radially restrict the swing of the clamping device 3 and the tail of the rocket engine, and does not restrict the axial movement of the rocket engine. Therefore, the design of this utility model does not affect the normal conduct of the thrust test of the rocket engine.

[0025] like Figure 4 It is a telescopic mechanism 41 installed on the upper support frame 11, such as Figure 5 The diagram shows a telescopic mechanism 41 installed on the lower support frame 12. Two telescopic mechanisms 41 have identical structures. Each telescopic mechanism 41 includes a cylinder 411, a screw shaft 412, and a telescopic shaft 413. The cylinder 411 is installed through and fixedly mounted on the central frame 1. The screw shaft 412 is rotatably connected to the cylinder 411, with a portion of the screw shaft 412 inserted inside the cylinder 411. The inserted end of the screw shaft 412 has a threaded section 4121. A portion of the telescopic shaft 413 is inserted into the cylinder 411 and threadedly connected to the threaded section 4121 of the screw shaft 412. The inserted portion of the telescopic shaft 413 matches the inner diameter of the cylinder 411. A guide groove 4131 is provided on the outer wall of the telescopic shaft 413. A guide screw 414 is threaded onto the outer wall of the cylinder 411, with the end of the guide screw 414 extending into the cylinder. The telescopic shaft 413 is inserted into the guide groove 4131. A limiting roller 42 is rotatably installed at the end of the telescopic shaft 413 on the outside of the cylinder 411. The screw shaft 412 is provided with a screw head 4122 at the end of the screw shaft 412 on the outside of the cylinder 411. The screw shaft 412 can be rotated by screwing the screw head 4122. Since the guide screw 414 is inserted into the guide groove 4131, the telescopic shaft 413 cannot rotate. When the screw shaft 412 rotates, the telescopic shaft 413 can only achieve linear telescopic movement. The linear telescopic movement of the telescopic shaft 413 can form the telescopic movement effect of the limiting roller 42. The telescopic movement stroke of the limiting roller 42 is determined by the length of the guide groove 4131. In this utility model, the length of the guide groove 4131 should meet the requirement that the telescopic stroke of the limiting roller 42 is not less than 60mm.

[0026] like Figure 1 and Figure 2As shown, the screw shafts 412 of the two radial limiting devices 4 installed on the upper support frame 11 have exposed screw heads 4122, providing operating space. They can be directly connected to handwheels 43 for operation assistance. However, the two radial limiting devices 4 on the lower support frame 12 do not have operating space. Therefore, this invention provides two manual operation holes 121 on the lower support frame 12. The two manual operation holes 121 are respectively set to correspond to the two radial limiting devices 4 installed on the lower support frame 12. The screw heads 4122 of the screw shafts 412 of the two radial limiting devices 4 extend into the manual operation holes 121. The manual operation holes 121 are not large enough to install handwheels 43, but the screw heads 4122 can be turned by tools such as socket wrenches.

[0027] Once the central frame 1 of this utility model is assembled, its overall weight is very heavy, therefore... Figure 1 As shown, two symmetrically arranged lifting lugs 111 are fixedly connected to the top of the upper support frame 11, and the central frame 1 is hoisted as a whole by means of overhead crane.

[0028] like Figure 1 and Figure 2 As shown, the lower support frame 12 is provided with two symmetrically arranged support legs 122. The bottom of the support legs 122 is connected to a flange base plate 123. The support legs 122 are fixedly connected to the test trolley through the flange base plate 123 (the test trolley is used to support the horizontally lying rocket engine. This utility model needs to be fixed to the test trolley to radially position the tail of the horizontally lying rocket engine).

[0029] The above description is merely a preferred embodiment of this utility model. The protection scope of this utility model is not limited to the above embodiments. All technical solutions falling within the scope of this utility model's concept are protected. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principle of this utility model should also be considered within the protection scope of this utility model.

Claims

1. A central positioning frame, characterized in that, The device includes a central frame (1) and a clamping device (3). The central frame (1) has a circular through-hole positioning cavity (2). The clamping device (3) is fixedly installed at the tail of the rocket engine and is inserted into the positioning cavity (2). Several radial limiting devices (4) are installed on the central frame (1). The several radial limiting devices (4) are evenly distributed around the positioning cavity (2). The radial limiting device (4) includes a rotatably installed limiting roller (42). The limiting roller (42) abuts against the outer wall of the clamping device (3).

2. The center positioning frame according to claim 1, characterized in that, The central frame (1) includes an upper support frame (11) and a lower support frame (12), which are stacked and connected to form a positioning cavity (2).

3. The center positioning frame according to claim 1, characterized in that, The clamping device (3) includes an upper semicircular body (31) and a lower semicircular body (32), which are fixedly connected by bolts. Two rings of reinforcing ribs (33) are vertically welded on the outer walls of the upper semicircular body (31) and the lower semicircular body (32), respectively located at both ends of the upper semicircular body (31) and the lower semicircular body (32) in the width direction.

4. The center positioning frame according to claim 1, characterized in that, The radial limiting device (4) is installed in a quantity of four. The outer wall of the clamping device (3) is provided with several notch areas (34), and the notch areas (34) are set one-to-one with the radial limiting device (4).

5. A center positioning frame according to claim 1, characterized in that, The radial limiting device (4) further includes a telescopic mechanism (41), which is installed through the central frame (1), and the limiting roller (42) is rotatably connected to the telescopic mechanism (41).

6. A center positioning frame according to claim 5, characterized in that, The telescopic mechanism (41) includes a cylinder (411), a screw shaft (412), and a telescopic shaft (413). The cylinder (411) is inserted through and fixedly installed on the central frame (1). The screw shaft (412) is rotatably connected to the cylinder (411). The screw shaft (412) is partially inserted into the cylinder (411), and the insertion end of the screw shaft (412) is provided with a threaded section (4121). The telescopic shaft (413) is partially inserted into the cylinder (411) and is connected to the screw shaft (412). The telescopic shaft (413) is threaded to the threaded section (4121). A guide groove (4131) is provided on the outer wall of the telescopic shaft (413). A guide screw (414) is threaded on the outer wall of the cylinder (411). The end of the guide screw (414) extends into the guide groove (4131). A limit roller (42) is rotatably installed on the end of the telescopic shaft (413) on the outside of the cylinder (411). The end of the screw shaft (412) on the outside of the cylinder (411) is provided as a screw head (4122).

7. A center positioning frame according to claim 2, characterized in that, Two radial limiting devices (4) installed on the upper support frame (11) have a handwheel (43) fixedly connected to the screw shaft (4122) of the screw shaft (412). Two manual operation holes (121) are opened on the lower support frame (12). The two manual operation holes (121) are respectively set to correspond to the two radial limiting devices (4) installed on the lower support frame (12). The screw shaft (4122) of the two radial limiting devices (4) extends into the manual operation hole (121).

8. A center positioning frame according to claim 2, characterized in that, The top of the upper support frame (11) is fixedly connected to two symmetrically arranged lifting lugs (111).

9. A center positioning frame according to claim 2, characterized in that, The lower support frame (12) is provided with two symmetrically arranged legs (122), and the bottom of the legs (122) is connected to a flange base plate (123).

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