A radial track control nozzle thrust test device and test method

Abstract

The present invention provides a radial track control nozzle thrust test device and test device, wherein a base plate is fixedly connected to a bearing shaft, and both ends of the bearing shaft are installed on the base plate through bearing seats; two adjustment screws are symmetrically arranged on the base plate with the axis of the bearing shaft as the symmetry axis, and the adjustment screws change the distance from the base plate through their own rotation, and the base plate is ensured to be in a horizontal position through the two adjustment screws; the bottom of the attitude and track control engine gas generator is installed on the base plate; the attitude and track control engine track control nozzle is provided with a nozzle connecting rod, a thrust sensor, a ball head and a ball head seat connected in sequence, and the ball head seat is supported on a bearing wall perpendicular to the base plate, and when the track control nozzle is working, a flame is ejected from the track control nozzle, and the thrust generated is transmitted to the thrust sensor through the nozzle connecting rod. The present invention has a simple structure, is easy to install and debug, can effectively improve the accuracy of thrust testing, and shortens the preparation time of the entire thrust test.

Description

Technical Field

[0001] The invention relates to a thrust test device and a test method, and belongs to the technical field of thrust test of solid attitude and orbit control engines. Background Art

[0002] As a key executive component for missile directional control, the attitude and orbit control engine is a power device that improves the missile's advanced maneuverability. It provides orbit control force for the missile during flight, giving the missile high maneuverability.

[0003] The thrust output axis of the orbit control nozzle of the attitude and orbit control engine is usually perpendicular to the engine axis. The gas generated by the gas generator is ejected through the orbit control nozzle, generating direct radial force, thereby changing the orbit of the projectile.

[0004] The thrust output axis of the nozzle of a traditional solid rocket engine is along the engine axis. The thrust of a traditional solid rocket engine can be tested by placing the solid rocket engine horizontally on a radial support device and arranging thrust sensors along the engine axis. However, the solid gas attitude and orbit control engine is different from the traditional solid rocket engine. The direction of its nozzle thrust is perpendicular to the engine axis, which makes it impossible to test the attitude / orbit control nozzle output thrust using the traditional solid rocket engine thrust test method. Summary of the invention

[0005] In order to overcome the shortcomings of the prior art, the present invention provides a radial orbit control nozzle thrust test device, which vertically places the attitude and orbit control engine on a device that can rotate along the thrust direction, and directly connects the orbit control nozzle through a thrust sensor to perform thrust testing.

[0006] The technical solution adopted by the present invention to solve the technical problem is: a radial track control nozzle thrust test device, including a bearing seat, a load-bearing shaft, a base plate, an adjustment screw, a base plate and a thrust sensor.

[0007] The base plate is fixedly connected to the load-bearing shaft, and both ends of the load-bearing shaft are installed on the base plate through bearing seats; two adjustment screws are symmetrically arranged on the base plate with the axis of the load-bearing shaft as the axis of symmetry, and the adjustment screws change the distance from the base plate by their own rotation, and the base plate is ensured to be in a horizontal position by the two adjustment screws; the bottom of the attitude and track control engine gas generator is installed on the base plate; the attitude and track control engine track control nozzle is provided with a nozzle connecting rod, a thrust sensor, a ball head and a ball head seat connected in sequence, and the ball head seat is pressed against a load-bearing wall perpendicular to the base plate. When the track control nozzle is working, flames are ejected from the track control nozzle, and the thrust generated is transmitted to the thrust sensor through the nozzle connecting rod.

[0008] The present invention also provides a method for radial track control nozzle thrust test, comprising the following steps: installing an attitude and track control engine on a test device, rotating two adjustment screws to ensure that the two adjustment screws are in contact with a base plate but do not interact with each other, thereby playing a supporting and protective role; adjusting the output end position of a thrust calibration device to ensure that the output end axis is aligned with the track control nozzle outlet axis, and then applying a standard force to calibrate the thrust sensor; when the track control nozzle is working, a flame is ejected from the track control nozzle, and the generated thrust is transmitted to the thrust sensor through a nozzle connecting rod, thereby completing the thrust test.

[0009] The beneficial effects of the present invention are:

[0010] 1) The present invention provides a radial orbit control nozzle thrust test device, wherein the attitude and orbit control engine is installed on a base plate, and the base plate is connected to the test bench through a load-bearing shaft, a bearing seat and a lower base plate, so that the engine and the base plate can rotate along the load-bearing shaft as a whole, and the base plate can be adjusted to a horizontal position through two vertical adjustment screws between the base plate and the base plate, ensuring that the nozzle output shaft coincides with the sensor shaft, and the thrust test data is accurate.

[0011] 2) The radial orbit control nozzle thrust test device provided by the present invention has a simple structure, is easy to install and debug, and is easy to install and disassemble the attitude and orbit control engine.

[0012] 3) The radial track control nozzle thrust test device and test method provided by the present invention can perform in-situ calibration of the sensor, effectively improve the thrust test accuracy, and effectively shorten the preparation time of the entire thrust test. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a structural schematic diagram of a thrust testing device in a preferred embodiment of the present invention;

[0014] Figure 2 This is a structural schematic diagram of an attitude and orbit control engine of the present invention installed on the thrust testing device;

[0015] In the figure, 1-base plate, 2-bearing seat, 3-load-bearing shaft, 4-base plate, 5-adjusting screw, 6-bearing seat connecting screw, 7-base plate connecting screw, 8-nozzle connecting rod, 9-thrust sensor, 10-ball head, 11-ball head seat. DETAILED DESCRIPTION

[0016] The present invention is further described below in conjunction with the accompanying drawings and embodiments. The present invention includes but is not limited to the following embodiments.

[0017] The present invention proposes a radial track control nozzle thrust test device and test method, which solves the problem of accurate measurement of radial track control nozzle thrust. The test device and test method mainly realize accurate measurement of radial track control nozzle thrust by designing a radial track control nozzle thrust test device and using a reliable thrust transmission structure. The whole device is easy to calibrate and the test device preparation time is short.

[0018] The technical solution provided by the present invention is as follows:

[0019] In the first aspect, a radial track control nozzle thrust test device is provided, wherein the track control nozzle of the attitude and track control engine is perpendicular to the axial direction of the gas generator, the attitude and track control engine is installed on the thrust test device, and the thrust test device includes a bearing seat, a load-bearing shaft, a base plate and a base plate, the attitude and track control engine is installed on the base by screws, the tooling as a whole is connected to the test bench through a lower base plate, and the engine and base connection structure can rotate along the load-bearing shaft; wherein,

[0020] The test bench is connected and tightened with bolts, the base plate and the bearing seat are connected and fixed by a bolt and nut structure, an integral shaft sleeve is installed on the bearing seat, and the load-bearing shaft is inserted into the integral shaft sleeve; the base plate and the load-bearing shaft are connected by six bolts; the base plate and the bolt connections on the base plate are designed as step holes to ensure that the end faces are not protruding; 8 through holes are designed on the base plate for connection with the flange at the bottom of the attitude and orbit control engine gas generator; two threaded holes are designed at symmetrical positions on both sides of the base plate, and two adjustment screws are installed. The horizontality of the base plate is adjusted by adjusting the screws to ensure that the thrust output axis of the orbit control nozzle is parallel to the base plate.

[0021] After the base plate is adjusted to horizontal, the thrust output shaft of the track-controlled nozzle is perpendicular to the central axis of the gas generator; the rear end of the track-controlled nozzle is connected to the nozzle connecting rod, thrust sensor, ball head and ball head seat, and the ball head seat is against the load-bearing wall. After adjustment into place, the two adjustment screws are rotated toward the base plate to ensure that it is in contact with the base plate but without interaction, thereby playing a supporting and protective role; when the track-controlled nozzle is working, the flame is ejected from the track-controlled nozzle, and the thrust generated is transmitted to the thrust sensor through the nozzle connecting rod and supported by the load-bearing wall.

[0022] In a second aspect, a radial orbit control nozzle thrust test method includes: installing an attitude and orbit control engine on a test fixture, and fastening and connecting the fixture, a load-bearing wall, and the attitude and orbit control engine after optimal positions are determined;

[0023] After the thrust sensor is adjusted into place, it is calibrated in situ. The specific method is as follows: install the thrust calibration device at the front end of the attitude and orbit control engine; adjust the output end position of the thrust calibration device to ensure that the output end axis is aligned with the orbit control nozzle outlet axis, and then apply a standard force to calibrate the thrust sensor.

[0024] The embodiment of the present invention provides a radial track control nozzle thrust test tool, the structure of which is as follows: Figure 1 As shown, it includes a base plate 1, a bearing seat 2, a load-bearing shaft 3, a base plate 4, an adjustment screw 5, a bearing seat connecting screw 6, and a base plate connecting screw 7.

[0025] Insert the left and right ends of the load-bearing shaft 3 into the bearing seat 2 respectively, and then connect and fix the bearing seat 2 and the base plate 1 through the bearing seat connecting screws 6; vertically install the adjustment screw 5 at the corresponding installation position of the base plate, and then install the base plate 4 on the load-bearing shaft 3, and connect and fix it with the base plate connecting screws 7.

[0026] The base plate 1 is connected to the test bench by bolts, and the adjusting screws 5 are used to adjust the levelness of the base plate 4 to ensure accurate testing.

[0027] The attitude and orbit control engine described in the embodiment of the present invention is installed on a test bench, and its structure is as follows: Figure 2 As shown, the attitude and orbit control engine is connected to the base plate 4 through the base plate connecting screws 7, and the rear end of the orbit control nozzle is installed with a nozzle connecting rod 8, a thrust sensor 9, a ball head 10 and a ball head seat 11.

[0028] The axis of the nozzle connecting rod 8 is colinear with the thrust output axis of the track-controlled nozzle. Threads are designed at both ends of the thrust sensor 9. One end is connected to the nozzle connecting rod 8, and the other end is connected to the ball head 10. By adjusting the positions of various components, the ball head 10 extends into the ball head seat 11, and the other end of the ball head seat 11 contacts the load-bearing wall to ensure reliable support during thrust output.

[0029] After the overall structure is installed, the test fixture is fixed to the test bench by bolts, and then the adjustment screw 5 is fine-tuned to ensure that the adjustment screw 5 is in contact with the base plate 4 but not subjected to force.

[0030] When the track control nozzle described in this embodiment is working, the thrust it generates is transmitted to the thrust sensor 9 through the nozzle connecting rod 8, and the output thrust of the nozzle can be accurately measured.

Claims

1. A radial track control nozzle thrust test device, comprising a bearing seat, a load-bearing shaft, a base plate, an adjustment screw, a base plate and a thrust sensor, characterized in that: The base plate is fixedly connected to the load-bearing shaft, and both ends of the load-bearing shaft are installed on the base plate through bearing seats; two adjustment screws are symmetrically arranged on the base plate with the axis of the load-bearing shaft as the axis of symmetry, and the adjustment screws change the distance from the base plate by their own rotation, and the two adjustment screws are used to ensure that the base plate is in a horizontal position, and to ensure that the thrust output axis of the track control nozzle is parallel to the base plate; the bottom of the attitude and track control engine gas generator is installed on the base plate; the attitude and track control engine track control nozzle is provided with a nozzle connecting rod, a thrust sensor, a ball head and a ball head seat connected in sequence, and the ball head seat is supported on a load-bearing wall perpendicular to the base plate. When the track control nozzle is working, flames are ejected from the track control nozzle, and the thrust generated is transmitted to the thrust sensor through the nozzle connecting rod; the track control nozzle of the attitude and track control engine is perpendicular to the axial direction of the gas generator.

2. A method for testing the thrust of a radially track-controlled nozzle using the device of claim 1, characterized in that: The following steps are involved: Install the attitude and orbit control engine on the test device, rotate the two adjustment screws to ensure that both adjustment screws are in contact with the base plate but without interaction, so as to play a supporting and protective role; adjust the output end position of the thrust calibration device to ensure that the output end axis is aligned with the orbit control nozzle outlet axis, and then apply a standard force to calibrate the thrust sensor; when the orbit control nozzle is working, the flame is ejected from the orbit control nozzle, and the thrust generated is transmitted to the thrust sensor through the nozzle connecting rod, thereby completing the thrust test.

Images