Plume baffle device and method for attitude control nozzle thrust non-contact measurement

Abstract

The invention discloses a plume baffle device and method for attitude control nozzle thrust non-contact measurement, and belongs to the field of engine test. The device comprises a plume baffle, a dynamic indirect force transducer and a mounting bracket. The mounting bracket is fixed on one side of the multi-component test bed, the plume baffle is coaxially and fixedly connected with the dynamic indirect force transducer, the inclined surface of the plume baffle faces the attitude and orbit control engine to be tested and is coaxial with the attitude control spray pipe, and the dynamic indirect force transducer is fixed on the mounting bracket. The plume baffle bears plume impact of the attitude control spray pipe, the dynamic indirect force measurement sensor measures the impact force borne by the plume baffle, and a measurement result is fed back to the upper computer for processing. The device is used in cooperation with a multi-component thrust vector test system, and by establishing the corresponding relation between the thrust of the attitude control spray pipe and the impact force of the plume baffle, the test problems that in the thrust vector test of the solid attitude and orbit control engine, the thrust of the orbit control spray pipe and the thrust of the attitude control spray pipe influence each other, and the thrust test error of the attitude control spray pipe is large are solved.

Description

Technical Field

[0001] The present invention belongs to the field of engine testing, and specifically relates to a plume baffle device and method for non-contact measurement of attitude control nozzle thrust, which is mainly used for thrust vector testing of solid attitude and orbit control engines, and can accurately measure the thrust characteristics of the attitude control nozzle when the solid attitude and orbit control engine work in coordination. Background Art

[0002] Solid attitude and orbit control engines are mainly used to control the attitude of the aircraft. When working, the attitude control nozzle and orbit control nozzle generate continuous pulse thrust, and the thrust generated by the orbit control nozzle is nearly 10 times greater than that generated by the attitude control nozzle. It is required to measure the attitude control thrust vector and orbit control thrust vector separately when the orbit control and attitude control nozzles work together. Since both the orbit control nozzle and the attitude control nozzle are connected to the same combustion rigid shell, it is a technical problem to analyze the two thrust vectors.

[0003] In the existing multi-component force test, a multi-component thrust vector test system is generally used to perform thrust vector test, such as Figure 1 As shown, during the test, the multi-component force test bench is fixed on the test platform, the multi-component force measuring assembly (a sensor for directly testing the thrust of the attitude and orbit control engine) is installed on the multi-component force test bench, and then the attitude and orbit control engine to be tested is fixedly installed on the multi-component force measuring assembly through the adapter tooling. The engine is working, and the thrust vectors of the X, Y, and Z axes are tested through the multi-component force measuring assembly. Then, according to the installation position of the test product on the multi-component force measuring assembly, the force measuring model of the corresponding multi-component force measuring assembly calculates the thrust of each nozzle. When the thrust output of the orbit control nozzle is much greater than the thrust of the attitude control nozzle, this test method is affected by the thrust of the orbit control nozzle, and the test thrust error of the attitude control nozzle is large, and the accuracy cannot meet the requirements. Summary of the invention

[0004] Technical problem to be solved: In order to avoid the deficiencies of the prior art, the present invention provides a plume baffle device and a test method for non-contact measurement of attitude control nozzle thrust. A plume baffle device is added to the existing multi-component thrust vector test system, and the corresponding relationship between the attitude control nozzle thrust and the plume baffle impact force is established by measuring the impact force of the plume ejected from the attitude control nozzle on the plume baffle. This solves the problem of mutual influence between the thrust of the orbit control nozzle and the attitude control nozzle in the thrust vector test of the solid attitude and orbit control engine, and the large test error of the attitude control nozzle thrust test.

[0005] The technical solution of the present invention is: a plume baffle device for non-contact measurement of attitude control nozzle thrust, used in conjunction with a multi-component thrust vector test system, comprising a plume baffle, a dynamic indirect force sensor and a mounting bracket;

[0006] The mounting bracket is fixed on the test platform and is located on one side of the multi-component force test bench;

[0007] The plume baffle and the dynamic indirect force sensor are coaxially fixedly connected in sequence, and one end of the dynamic indirect force sensor facing away from the plume baffle is fixed to the mounting bracket; one end of the plume baffle facing away from the dynamic indirect force sensor is an inclined surface, and the inclined surface of the plume baffle faces the attitude and orbit control engine to be measured;

[0008] The plume baffle is coaxial with an attitude control nozzle of the attitude and orbit control engine to be measured, and is used to bear the plume impact of the attitude control nozzle; the dynamic indirect force sensor is used to measure the impact force borne by the plume baffle, and is used to measure the thrust of the attitude control nozzle after calibration; the dynamic indirect force sensor is electrically connected to the data acquisition system of the multi-component thrust vector test system, and is used to transmit collected data to the data acquisition system; the data acquisition system is electrically connected to the host computer of the multi-component thrust vector test system, and the host computer is used for data processing.

[0009] A further technical solution of the present invention is: the mounting bracket includes a base, a vertical adjustment rod, a force-bearing seat and a transverse adjustment rod; the base is fixed on the test platform; the vertical adjustment rod is vertically fixed on the base; the force-bearing seat is installed on the vertical adjustment rod, and its installation height along the vertical adjustment rod is adjustable; the transverse adjustment rod is horizontally installed on the force-bearing seat, the transverse adjustment rod is coaxial with an attitude control nozzle of the attitude and orbit control engine to be measured, and the distance between the transverse adjustment rod and the coaxial attitude control nozzle is adjustable; the dynamic indirect force sensor is coaxially fixed on the end of the transverse adjustment rod facing the attitude and orbit control engine to be measured.

[0010] A further technical solution of the present invention is: the vertical adjustment rod is a cylindrical rod, two of which are respectively installed at the two ends of the base; a first through hole is provided at both ends of the force-bearing seat, which is used to horizontally fit the force-bearing seat on the two vertical adjustment rods; slots are provided at both ends of the force-bearing seat along the axial direction of the first through hole and through the first through hole, and the slot divides the force-bearing seat outside the first through hole into two equal halves, and screws are passed through the force-bearing seats on both sides of the slot to lock the installation height of the force-bearing seat along the vertical adjustment rod.

[0011] A further technical solution of the present invention is: a second through hole perpendicular to the surface where the two vertical adjustment rods are located is provided at the center of the force-bearing seat, and the transverse adjustment rod is horizontally installed in the second through hole; the transverse adjustment rod is arranged in a line along the axial direction and has multiple equally spaced threaded holes, and the force-bearing seat is provided with at least two threaded holes corresponding to the threaded holes of the transverse adjustment rod and passing through the second through hole, and a locking screw is inserted into the threaded holes of the force-bearing seat and the transverse adjustment rod to lock the position of the transverse adjustment rod.

[0012] A further technical solution of the present invention is: the plume baffle is a cylinder with an inclined surface at one end, and a threaded hole is axially arranged at the center of the surface opposite to the inclined surface; threaded holes are coaxially arranged at the centers of both ends of the dynamic indirect force sensor; a threaded hole is axially arranged at the center of one end of the lateral adjustment rod facing the attitude control nozzle; the plume baffle and the dynamic indirect force sensor, and the dynamic indirect force sensor and the lateral adjustment rod are all connected and fixed by studs.

[0013] A further technical solution of the present invention is: the inclination angle of the inclined surface of the plume baffle is φ, the distance between the center point of the inclined surface and the outer end surface of the coaxial attitude control nozzle is L, and the diameter, inclination angle φ and distance L of the plume baffle are all determined according to the specifications and models of the attitude and orbit control engine to be measured.

[0014] A method for measuring and using the plume baffle device for non-contact measurement of attitude control nozzle thrust comprises the following steps:

[0015] Step 1, calibration installation preparation; using the multi-component thrust vector test system, replace the attitude and orbit control engine to be tested installed on the adapter with the attitude and orbit control engine simulation shell, and connect the cold air test system and the simulation shell through a hose; select the corresponding plume baffle according to the output force value of the attitude control nozzle of the simulation shell, install the plume baffle device, make the plume baffle and one attitude control nozzle of the simulation shell facing coaxial and adjust the distance L, and close the remaining attitude control nozzles;

[0016] Step 2: calibrate the dynamic indirect force sensor to establish the corresponding relationship between the attitude control nozzle thrust and the impact force on the plume baffle;

[0017] Step 2.1: Divide the maximum thrust value of the dynamic indirect force sensor to be calibrated into i steps at equal intervals, which are used as the preset thrust input value during calibration, denoted as X i , where i = 1, 2, ~ k, i is the i-th calibration point, k is the number of calibration points;

[0018] Step 2.2, controlling the cold air test system so that the thrust of the gas flow rate ejected from a single attitude control nozzle on the multi-component force measuring assembly reaches a preset thrust value X1;

[0019] At this time, the indirect force sensor measures the thrust Y on the plume baffle: c11 The measured data are transmitted to the data acquisition system of the multi-component thrust vector test system, and the host computer of the multi-component thrust vector test system analyzes and processes the collected data to establish the X1 and Y c11 The corresponding relationship;

[0020] Step 2.3: Follow the steps in step 2.2 to make the thrust of the single attitude control nozzle reach the preset thrust values ​​X1, X2, X3, and X4 in the ascending order of the forward direction.k The thrust on the plume baffle measured by the indirect force sensor is Y c11 , Y c21 , Y c31 ,~Y ck1 , establish X1, X2, X3, ~X k With Y c11 , Y c21 , Y c31 ,~Y ck1 One-to-one correspondence; Y ci1 The thrust measured by the indirect force sensor at the i-th calibration point during the first positive ascending calibration stroke, i = 1, 2, ~ k;

[0021] Then, the thrust of the single attitude control nozzle is calibrated in reverse descending order to reach the preset thrust value X k , ~X3, X2, X1, the thrust on the plume baffle measured by the indirect force sensor is Y fk1 ,~Y f31 , Y f21 , Y f11 , establish X1, X2, X3, ~X k With Y fk1 ,~Y f31 , Y f21 , Y f11 One-to-one correspondence; Y fi1 is the thrust measured by the indirect force sensor at the i-th calibration point during the first reverse descending stroke, i = 1, 2, ~ k;

[0022] Step 2.4, repeat step 2.3, repeat the forward ascending stroke calibration and the reverse descending stroke calibration R times, and obtain multiple sets of test data Y of the indirect force sensor at each calibration point cij and Y fij , where j is the number of forward and reverse strokes, j = 1, 2, ~ R;

[0023] Step 2.5 Calculate the average and total average of the forward and reverse travel calibration data of each calibration point according to the following formula:

[0024]

[0025]

[0026] Where: is the average value of the forward travel calibration data of the i-th calibration point;

[0027] Y cij is the jth forward travel calibration data at the i-th calibration point;

[0028] is the average value of the reverse travel calibration data of the i-th calibration point;

[0029] Y fij is the jth reverse stroke calibration data at the i-th calibration point;

[0030] is the total average value of all calibration data of the i-th calibration point;

[0031] according to Data connection, forming a calibration curve of the dynamic indirect force sensor, and establishing the full range correspondence between the dynamic indirect force sensor and the multi-component force measurement assembly;

[0032] Step 3, measure the thrust output by the attitude control nozzle when the attitude and orbit control engine is working; remove the simulation shell, install the attitude and orbit control engine to be measured, align one attitude control nozzle coaxially with the plume baffle, ignite the attitude and orbit control engine, at this time, the thrust output by the attitude control nozzle when the attitude and orbit control engine is working can be measured by the dynamic indirect force sensor.

[0033] A further technical solution of the present invention is: after the step 2.5 is completed, a working straight line is established to replace the calibration curve of step 2.5, reflecting the relationship between the thrust measured by the dynamic indirect force sensor and the multi-component force measurement assembly, which is expressed as:

[0034] Y= a+bX (7)

[0035] Where: Y is the thrust value measured by the dynamic indirect force sensor,

[0036] X is the thrust value measured by the multi-component force measuring assembly,

[0037] a is the intercept of the working line on the Y axis,

[0038] b is the slope of the working straight line,

[0039] The working straight line is determined using the least squares method based on the calibration data collected in step 2.4.

[0040] A further technical solution of the present invention is: the number of the calibration points is five, k=5.

[0041] A further technical solution of the present invention is: the specifications of the attitude control nozzle of the attitude and orbit control engine to be tested replaced in step 3 are the same as the specifications of the attitude control nozzle of the simulation shell.

[0042] Beneficial Effects

[0043] The beneficial effects of the present invention are as follows: the plume baffle device and method for non-contact measurement of attitude control nozzle thrust described in the present invention can accurately measure the thrust output of the attitude control nozzle when the track and attitude are working together in the multi-component test of the solid attitude and orbit control engine. By being used in conjunction with the multi-component thrust vector test system, the thrust output of each nozzle when the attitude and orbit control engine is working is decoupled, thereby improving the accuracy of the attitude control nozzle thrust test when the track and attitude are working together.

[0044] Compared with the prior art, the advantages of the present invention include:

[0045] 1) The present invention realizes the thrust test of the attitude control nozzle through a non-contact test scheme: based on the real-time corresponding relationship between the force generated by the plume ejected from the attitude control nozzle acting on the plume baffle and the thrust of the attitude control nozzle, this relationship is used to characterize the thrust output of the attitude control nozzle by testing the impact force of the plume baffle. The thrust output of a single nozzle is accurately analyzed, solving the test problem of the solid attitude and orbit control engine that cannot decouple the two thrust vectors when the orbit control nozzle and the attitude control nozzle output thrust at the same time. The present invention avoids the errors caused by the coupling factors between the test bench (including the multi-component test bench, the test platform, the adapter tooling, etc.) and the product to be tested, the sensor, etc. in the existing direct testing process using the multi-component thrust vector test system, as well as the technical problem that the attitude control nozzle is difficult to respond to when the high frequency output.

[0046] 2) The plume baffle device can well capture the impact force generated by the plume, and can select plume baffles of corresponding diameter and inclination angle according to the throat size and maximum thrust of the attitude control nozzle, and adjust the appropriate test distance L, so as to calibrate different attitude control nozzles. After calibration, the thrust change generated by the attitude control nozzle of this specification when the attitude and orbit control engine is working can be accurately tested. At the same time, the distance between the center of the inclined surface of each plume baffle and the bottom surface can be kept unchanged, so as to better control the distance L between the plume baffle and the attitude control nozzle. In this way, for attitude control nozzles with different thrusts, only plume baffles with different inclination angles need to be replaced, which ensures the test accuracy and simplifies the test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] Figure 1 It is a schematic diagram of the installation of the plume baffle device and the multi-component thrust vector test system in the embodiment of the present invention;

[0048] Figure 2 Schematic diagram of force analysis of a plume baffle in an embodiment of the present invention;

[0049] Figure 3 Schematic diagram of plume baffles with different slope angles in an embodiment of the present invention;

[0050] Figure 4 Schematic diagram of the connection between the plume baffle device, the data acquisition system and the host computer in the embodiment of the present invention.

[0051] Explanation of the accompanying drawings: 1-multi-component force test bench, 2-multi-component force measuring assembly, 3-adaptation tooling, 4-attitude and orbit control engine, 5-attitude control nozzle, 6-plume baffle, 61-inclined surface of plume baffle, 62-bottom surface of plume baffle, 7-dynamic indirect force sensor, 8-locking screw, 9-lateral adjustment rod, 10-load bearing seat, 101-first through hole, 102-slot, 103-second through hole, 11-vertical adjustment rod, 12-base, 13-test platform, 14-data acquisition system, 15-host computer, 16-plume ejected from the attitude control nozzle. DETAILED DESCRIPTION

[0052] The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, but should not be construed as limiting the present invention.

[0053] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0054] This embodiment provides a plume baffle device for non-contact measurement of attitude control nozzle thrust, which is used in conjunction with the existing multi-component thrust vector test system to achieve indirect testing and characterization of attitude control nozzle thrust by measuring the impact force of the plume baffle in the device without contacting and interfering with the normal operation of the solid attitude and orbit control engine, thereby improving the dynamic test performance of the attitude control nozzle thrust output, thereby achieving fast response, high-precision testing and characterization of the dynamic thrust vector of the solid attitude and orbit control engine. The thrust output of a single nozzle is accurately analyzed, solving the test problem of the inability to decouple the two thrust vectors when the orbit control nozzle and the attitude control nozzle output thrust at the same time for the solid attitude and orbit control engine.

[0055] See also Figure 1 The present embodiment provides a plume baffle device for non-contact measurement of attitude control nozzle thrust, comprising a plume baffle 6, a dynamic indirect force sensor 7, a lateral adjustment rod 9, a force bearing seat 10, a vertical adjustment rod 11 and a base 12. The plume baffle device is installed on a test platform 13 of a multi-component thrust vector test system, and is located on one side of a multi-component test bench 2.

[0056] In the multi-component thrust vector test system, the test platform 13 is a high-precision cast iron test platform; the multi-component test bench 2 is a support frame, the bottom of which is fixedly connected to the test platform 13, and the top of which is installed with a multi-component force measuring assembly 2; the multi-component force measuring assembly 2 is a sensor for directly measuring the thrust of the nozzle of the attitude and orbit control engine 4, the lower end of which is coaxially fixedly connected to the multi-component test bench 2, and the upper end is coaxially installed with a transfer fixture 3; the attitude and orbit control engine 4 is horizontally and coaxially fixed on the transfer fixture 3 with the transfer fixture, and the transfer fixture 3 is used to connect the attitude and orbit control engine 4 to be tested and the multi-component force measuring assembly 2; the multi-component force measuring assembly 2 is electrically connected to the data acquisition system 14 in the multi-component thrust vector test system, transmits the collected thrust data of the attitude and orbit control engine 4 to it, and processes and stores the data through the host computer 15 of the test system. In this embodiment, the host computer is a computer.

[0057] The base 12 in the plume baffle device is fixed to the test platform 13 by fasteners, and the vertical adjustment rod 11 is vertically fixed to the base 12. The vertical adjustment rod 11 is a cylindrical rod, and two are provided, which are arranged in a line and fixedly installed at both ends of the base 12, and the two vertical adjustment rods 11 are equidistant from the attitude and orbit control engine 4.

[0058] The force-bearing seat 10 is horizontally mounted on two vertical adjustment rods 11, and the installation height along the vertical adjustment rods 11 is adjustable. Specifically, first through holes 101 are provided at both ends of the force-bearing seat 10, and the aperture of the first through hole 101 matches the diameter of the vertical adjustment rod 11, so that the force-bearing seat 10 can be mounted on the two vertical adjustment rods 11. Notches 102 are provided at both ends of the force-bearing seat 10 along the axial direction of the first through hole 101 and through the first through hole 101, and the notch 102 divides the force-bearing seat 10 on the outside of the first through hole 101 into two equal halves. Threaded holes are provided on the force-bearing seat 10 on both sides of the notch 102, and screws are passed through the force-bearing seat 10 on both sides of the notch 102 to tighten the notch 102, thereby locking the installation height of the force-bearing seat 10 along the vertical adjustment rod 11. When the installation height of the bearing seat 10 is adjusted, the screws of the notches 102 on both sides are loosened and tightened, so that the bearing seat 10 can move up and down along the vertical adjustment rod 11. When the adjustment is in place, the screws at the notches 102 are locked again.

[0059] The lateral adjustment rod 9 is horizontally mounted on the bearing seat 10. The lateral adjustment rod 9 is coaxial with an attitude control nozzle 5 of the attitude and orbit control engine 4 to be measured, and the distance between the lateral adjustment rod 9 and the coaxial attitude control nozzle 5 can be adjusted. Specifically, the center of the bearing seat 10 is provided with a second through hole 103 perpendicular to the plane where the two vertical adjustment rods 11 are located, and the lateral adjustment rod 9 is horizontally installed in the second through hole 103. A plurality of threaded holes with equal spacing are arranged in a line along the axial direction above the outer diameter of the lateral adjustment rod 9. Correspondingly, two threaded holes corresponding to the threaded holes of the lateral adjustment rod 11 and passing through the second through hole 103 are provided on the bearing seat 10. The locking screw 8 is sequentially inserted into the threaded holes of the bearing seat 10 and the lateral adjustment rod 9 and is threadedly connected thereto, thereby locking the position of the lateral adjustment rod 9. By adjusting the connection hole position of the locking screw 8 on the lateral adjustment rod 9, the distance between the lateral adjustment rod 9 and the coaxial attitude control nozzle 5 can be adjusted.

[0060] The plume baffle 6 and the dynamic indirect force sensor 7 are coaxially fixedly connected in sequence, and are coaxially installed at the end of the lateral adjustment rod 9 facing the end of the attitude and orbit control engine 4 to be measured. The plume baffle 6 is coaxial with an attitude control nozzle 5 of the attitude and orbit control engine 4 to be measured, and is used to bear the plume impact of the attitude control nozzle 5. The dynamic indirect force sensor 7 is used to measure the impact force borne by the plume baffle 6, and is used to measure the real thrust of the attitude control nozzle 5 after calibration.

[0061] Specifically, Figure 3 As shown, the plume baffle 6 is a cylinder with an inclined surface 61 at one end, and the inclined surface 61 of the plume baffle 6 faces an attitude control nozzle 5 of the attitude and orbit control engine 4 to be measured. The side opposite to the inclined surface 61 is the bottom surface 62 of the plume baffle 6, and a threaded hole is provided in the center of the bottom surface 62 along the axial direction of the plume baffle 6 for fixed connection with the dynamic indirect force sensor 7. It should be noted that the plume baffle 6 can also be other shapes with inclined surfaces, but the cylindrical shape is optimal for the linear relationship of the nozzle of the solid attitude and orbit control engine, so the plume baffle 6 in this embodiment adopts a cylinder. Threaded holes are provided at the center positions of both ends of the dynamic indirect force sensor 7 along its axial direction, and the threaded hole at one end is fixedly connected to the bottom surface 62 of the plume baffle 6 through a stud, and the threaded hole at the other end is fixedly connected to the lateral adjustment rod 9 through another stud; the lateral adjustment rod 9 is provided with a threaded hole at the center position facing one end of the attitude control nozzle 5 along its axial direction.

[0062] The dynamic indirect force sensor 7 is electrically connected to the data acquisition system 14 of the multi-component thrust vector test system, and is used to transmit the collected data to the data acquisition system 14. The data acquisition system 14 is electrically connected to the host computer 15 of the multi-component thrust vector test system, and the host computer 15 is used for data processing and storage.

[0063] See also Figure 2The present invention adopts a non-contact measurement method, based on the real-time corresponding relationship between the force generated by the plume ejected from the attitude control nozzle acting on the plume baffle 6 and the thrust of the attitude control nozzle 5. By using this relationship, the thrust output of the attitude control nozzle 5 can be characterized by testing the impact force of the plume baffle 6.

[0064] The test principle is: the engine obtains thrust F by the reaction force of the high-speed airflow ejected backward, and the impact force of the plume ejected by the attitude control nozzle 5 is F'. F and F' are a pair of action and reaction forces, so they are equal in magnitude. The plume impacts the plume baffle 6, and the plume impact force on the plume baffle 6 is F". Due to plume loss and other reasons, F' and F" are not completely equal. The impact force F" on the plume baffle 6 can be divided into F parallel to the inclined surface 61 on the baffle r and F perpendicular to the inclined plane 61 n The angle between the inclined surface 61 of the plume baffle 6 and the vertical surface is the inclined surface inclination angle It is also the impact force F" on the plume baffle 6 and the F perpendicular to the slope. n The angle between b is the component force F perpendicular to the plume baffle 6 n The horizontal force component is as follows: Figure 2 shown.

[0065] F b It is related to the thrust F of the nozzle, so in the experiment, an indirect force sensor can be used to measure F b The value of is used to characterize the engine thrust F. The relationship between the engine thrust F and Fb measured by the indirect force sensor is:

[0066] F=F′ (1)

[0067] F′≈F″(2)

[0068]

[0069] During the test, F and F were tested simultaneously under different working conditions. b Measure and analyze the influence of various parameters on it, and obtain F and F b The relationship between can be used as the thrust correction formula for the thrust measurement device of the plume oblique baffle 6. In order to further simulate the three-dimensional flow field of the plume, a three-dimensional flow field calculation model of the nozzle plume is established, and the process of the gas ejected from the nozzle impacting the baffle is simulated. By changing the position, diameter, inclination angle of the plume baffle 6 and the nozzle inlet pressure and other parameters, the flow field under different working conditions is simulated and studied, and the optimal plume baffle diameter data and the distance data between the plume baffle and the attitude control nozzle are obtained. The corresponding baffle impact force is obtained to ensure that the impact force is within the optimal test range of the plume baffle and the indirect measurement sensor.

[0070] In this embodiment, the inclination angle of the inclined surface of the plume baffle 6 is The distance between the center point of the inclined surface 61 and the outer end surface of the coaxial attitude control nozzle 5 is L, and the diameter and inclination angle of the plume baffle 6 are The distance L is determined according to the specifications and models of the attitude and orbit control engine 4 to be measured, and the attitude control nozzle size and engine thrust need to be considered. within range to capture the plume.

[0071] Based on the above test principle, this embodiment also proposes a method for non-contact measurement of the attitude control nozzle thrust of a solid attitude and orbit control engine using the above-mentioned plume baffle device, which specifically includes the following steps:

[0072] Step 1: Calibrate and prepare for installation.

[0073] Using the multi-component thrust vector test system, a simulated casing with the same structure as the attitude and orbit control engine 4 to be tested is used to replace the attitude and orbit control engine 4 to be tested, and the simulated casing is installed on the adapter 3. The cold air test system and the simulated casing are connected through a hose. The cold air test system is a set of test control systems that simulates the working internal pressure of the attitude and orbit control engine, provides nitrogen medium gas with a timed steady-state pressure and mass flow rate into the engine simulated casing, and is used to verify the performance characteristics of various products of the solid engine under a specific working pressure environment, and can continuously output the flow through the nozzle of the engine simulated casing.

[0074] According to the output force value of the attitude control nozzle 5 of the simulated shell, select the corresponding diameter and inclination angle. The plume baffle 6 is installed, the plume baffle device is installed, the installation height of the bearing seat 10 and the installation position of the lateral adjustment rod 9 are adjusted, so that the plume baffle 6 and an attitude control nozzle 5 of the simulated shell facing it are coaxial, and the center of the inclined surface of the plume baffle 6 is ensured to be directly opposite to the axis of the coaxial attitude control nozzle 5, and the distance L meets the thrust requirements. The inner wall of the attitude control nozzle 5 and the surface of the plume baffle 6 are set as adiabatic non-slip wall surfaces. The attitude control nozzles in other directions except the working attitude control nozzle are closed, and a simulated shell of a single attitude control nozzle can also be used here. In addition, an attitude control engine with a single nozzle output can also be used instead of the simulated shell and the cold air test system, but since the engine charge is relatively wasteful, it is preferred to use a cold air test system to simulate the engine operation.

[0075] Step 2: calibrate the dynamic indirect force sensor 7 to establish a corresponding relationship between the thrust of the attitude control nozzle 5 and the impact force on the plume baffle 6.

[0076] Step 2.1: divide the maximum thrust value of the dynamic indirect force sensor 7 to be calibrated into i steps at equal intervals, which are used as the preset thrust input value during calibration. The input thrust is recorded as X i (Xi Right now Figure 2 F' in (i=1, 2, ~ k), where i is the i-th calibration point and k is the number of calibration points. In this embodiment, the number of calibration points is set to 5, k=5. For example, if the maximum test range of 500N needs to be calibrated, it can be divided into 5 step preset values ​​of 100N, 200N, 300N, 400N and 500N.

[0077] Step 2.2, control the cold air test system to make the preset pressure inside the simulated shell, so that the thrust of the gas flow ejected by the single working nozzle of the attitude control on the multi-component force measuring assembly 2 reaches the preset thrust value X1, such as 100N.

[0078] At this time, the indirect force sensor 7 measures the thrust Y on the plume baffle. c11 , (Y c11 Right now Figure 2 F b ) and transmit the measured data to the data acquisition system 14 of the multi-component thrust vector test system, and the host computer 15 of the multi-component thrust vector test system analyzes and processes the collected data to establish the X1 and Y c11 The corresponding relationship is automatically stored and recorded;

[0079] Step 2.3, according to the operation of step 2.2, the thrust of the single attitude control nozzle 5 reaches the preset thrust values ​​X1, X2, X3, X4, and X5 in the positive ascending sequence, and the dynamic indirect force sensor 7 measures the thrust of the plume baffle 6 to be Y c11 , Y c21 , Y c31 ,~Y ck1 , establish X1, X2, X3, ~X k With Y c11 , Y c21 , Y c31 ,~Y ck1 One-to-one correspondence; Y ci1 During the first positive ascending calibration stroke, the thrust measured by the dynamic indirect force sensor 7 at the i-th calibration point, i=1, 2, ~k, k=5.

[0080] Then, the thrust of the single attitude control nozzle 5 is calibrated in reverse descending order to reach the preset thrust value X k , ~X3, X2, X1, the thrust of the plume baffle 6 measured by the dynamic indirect force sensor 7 is Y fk1 ,~Y f31 , Y f21 , Y f11 , establish X1, X2, X3, ~X k With Y fk1 ,~Y f31 , Yf21 , Y f11 One-to-one correspondence; Y fi1 During the first reverse descending stroke, the thrust measured by the dynamic indirect force sensor 7 at the i-th calibration point, i=1, 2, ~k, k=5.

[0081] Step 2.4, repeat step 2.3, repeat the forward ascending stroke calibration and the reverse descending stroke calibration R times, and obtain multiple sets of test data Y of the dynamic indirect force sensor 7 at each calibration point cij and Y fij , where j is the number of forward and reverse strokes, j = 1, 2, ~ R; R is selected according to demand, the minimum is 1 time, the more repeated calibration times, the better the calibration accuracy. In order to ensure the accuracy of calibration, it is recommended to select R as 5.

[0082] Step 2.5, calculate the average and total average of the forward and reverse travel calibration data of each calibration point according to the following formula:

[0083]

[0084] Where: is the average value of the forward travel calibration data of the i-th calibration point;

[0085] Y cij is the jth forward travel calibration data at the i-th calibration point;

[0086] is the average value of the reverse travel calibration data of the i-th calibration point;

[0087] Y fij is the jth reverse stroke calibration data at the i-th calibration point;

[0088] is the total average value of all calibration data of the i-th calibration point;

[0089] By each The line formed by connecting the data is called the positive stroke calibration curve of the dynamic indirect force sensor 7; The line formed by connecting the data is called the reverse stroke calibration curve of the dynamic indirect force sensor 7. The line formed by connecting the data is called the calibration curve of the dynamic indirect force sensor 7, thereby establishing the full-range correspondence between the dynamic indirect force sensor 7 and the multi-component force measuring assembly 2.

[0090] Step 2.6, establish the working straight line of the indirect force sensor 7. For ease of use, a working straight line is used to replace the actual calibration curve obtained in step 2.5, and the working straight line is used to reflect the relationship between the thrust measured by the dynamic indirect force sensor 7 and the multi-component force measuring assembly 2. The working straight line of the indirect force sensor 7 can be expressed by the following characteristic equation:

[0091] Y= a+bX (7)

[0092] Where: Y is the thrust value measured by the dynamic indirect force sensor,

[0093] X is the thrust value measured by the multi-component force measuring assembly,

[0094] a is the intercept of the working line on the Y axis,

[0095] b is the slope of the working line,

[0096] The working straight line of the indirect force sensor 7 is determined by the least square method based on the calibration data collected in step 2.4.

[0097] Step 3, measure the thrust output by the attitude control nozzle when the attitude and orbit control engine is working; remove the simulation shell, install the attitude and orbit control engine 4 to be measured, the attitude control nozzle specifications of the attitude and orbit control engine 4 to be measured are the same as those of the simulation shell, and one attitude control nozzle 5 of the attitude and orbit control engine 4 to be measured is coaxially aligned with the plume baffle 6, and during this process, the plume baffle 6 remains stationary. The attitude and orbit control engine 4 is ignited and works. At this time, the thrust output by the attitude control nozzle 5 when the attitude and orbit control engine 4 is working can be measured by the dynamic indirect force sensor 7 according to the full-scale correspondence between the dynamic indirect force sensor 7 and the multi-component force measurement assembly 2 established in step 2.

[0098] The size parameters of the plume baffle device in the present invention are obtained through simulation calculation, and the process in which the engine nozzle ejects gas at high speed and impacts the inclined surface 61 of the plume baffle is simulated by numerical simulation method, and the flow field conditions under different plume baffle diameters, distances between the plume baffle and the attitude control nozzle, plume baffle inclination angles, nozzle outlet pressures and nozzle inlet pressures are simulated, and the influence of the above factors on the force of the plume baffle force measuring device is analyzed, and the force law curve of the plume baffle force measuring device is established. The force law and dynamic performance of the plume inclined baffle thrust test device are summarized, and the design parameters of the test device are obtained.

[0099] The plume baffle device and method for non-contact measurement of attitude control nozzle thrust provided by the present invention can measure the impact force of the plume baffle, establish the corresponding relationship between the nozzle thrust and the baffle impact force, and realize the inversion of the nozzle thrust through the measurement of the plume baffle impact force, so as to measure the thrust of the corresponding attitude control nozzle 5, obtain the plume flow field characteristics and the nozzle thrust association mechanism, realize the fast response and high precision test of the dynamic thrust vector of the solid attitude and orbit control engine, and realize the output decoupling of the orbit control thrust and the attitude control thrust of the attitude and orbit control engine. The problem of difficulty in high dynamic thrust vector test and multi-component force decoupling caused by the interference of the cross-linking force of the test bench and the limitation of the natural frequency of the thrust vector test is solved.

[0100] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and intent of the present invention.

Claims

1. A plume baffle device for non-contact measurement of attitude control nozzle thrust, characterized in that: For use with the multi-component thrust vectoring test system, including plume baffles, dynamic indirect force sensors and mounting brackets; The mounting bracket is fixed on the test platform and is located on one side of the multi-component force test bench; The plume baffle and the dynamic indirect force sensor are coaxially fixedly connected in sequence, and one end of the dynamic indirect force sensor facing away from the plume baffle is fixed to the mounting bracket; one end of the plume baffle facing away from the dynamic indirect force sensor is an inclined surface, and the inclined surface of the plume baffle faces the attitude and orbit control engine to be measured; The plume baffle is coaxial with an attitude control nozzle of the attitude and orbit control engine to be measured, and is used to bear the plume impact of the attitude control nozzle; the dynamic indirect force sensor is used to measure the impact force borne by the plume baffle, and is used to measure the thrust of the attitude control nozzle after calibration; the dynamic indirect force sensor is electrically connected to the data acquisition system of the multi-component thrust vector test system, and is used to transmit collected data to the data acquisition system; the data acquisition system is electrically connected to the host computer of the multi-component thrust vector test system, and the host computer is used for data processing.

2. The plume baffle device for non-contact measurement of attitude control nozzle thrust according to claim 1, characterized in that: The mounting bracket comprises a base, a vertical adjustment rod, a force-bearing seat and a transverse adjustment rod; the base is fixed on the test platform; the vertical adjustment rod is vertically fixed on the base; the force-bearing seat is installed on the vertical adjustment rod, and its installation height along the vertical adjustment rod is adjustable; the transverse adjustment rod is horizontally installed on the force-bearing seat, the transverse adjustment rod is coaxial with an attitude control nozzle of the attitude and orbit control engine to be measured, and the distance between the transverse adjustment rod and the coaxial attitude control nozzle is adjustable; the dynamic indirect force sensor is coaxially fixed to one end of the transverse adjustment rod facing the attitude and orbit control engine to be measured.

3. The plume baffle device for non-contact measurement of attitude control nozzle thrust according to claim 2, characterized in that: The vertical adjustment rod is a cylindrical rod, two of which are respectively installed at the two ends of the base; both ends of the force-bearing seat are provided with a first through hole, which is used to horizontally fit the force-bearing seat on the two vertical adjustment rods; both ends of the force-bearing seat are provided with a slot along the axial direction of the first through hole and passing through the first through hole, and the slot divides the force-bearing seat outside the first through hole into two equal halves, and screws are passed through the force-bearing seats on both sides of the slot to lock the installation height of the force-bearing seat along the vertical adjustment rod.

4. The plume baffle device for non-contact measurement of attitude control nozzle thrust according to claim 3, characterized in that: A second through hole perpendicular to the surfaces of the two vertical adjustment rods is provided at the center of the force-bearing seat, and the transverse adjustment rod is horizontally installed in the second through hole; the transverse adjustment rod is provided with a plurality of equally spaced threaded holes arranged in a line along the axial direction, and the force-bearing seat is provided with at least two threaded holes corresponding to the threaded holes of the transverse adjustment rod and passing through the second through hole, and a locking screw is inserted into the threaded holes of the force-bearing seat and the transverse adjustment rod to lock the position of the transverse adjustment rod.

5. The plume baffle device for non-contact measurement of attitude control nozzle thrust according to claim 4, characterized in that: The plume baffle is a cylinder with an inclined surface at one end, and a threaded hole is axially provided at the center of the surface opposite to the inclined surface; threaded holes are coaxially provided at the centers of both ends of the dynamic indirect force sensor; a threaded hole is axially provided at the center of one end of the lateral adjustment rod facing the attitude control nozzle; the plume baffle and the dynamic indirect force sensor, and the dynamic indirect force sensor and the lateral adjustment rod are all connected and fixed by studs.

6. The plume baffle device for non-contact measurement of attitude control nozzle thrust according to claim 5, characterized in that: The inclination angle of the inclined surface of the plume baffle is The distance between the center point of the inclined surface and the outer end surface of the coaxial attitude control nozzle is L, and the diameter and inclination angle of the plume baffle are The distance L is determined according to the specifications and models of the attitude and orbit control engine to be measured.

7. A method for measuring and using the plume baffle device for non-contact measurement of attitude control nozzle thrust according to claim 6, characterized in that: The following steps are involved: Step 1, calibration installation preparation; using the multi-component thrust vector test system, replace the attitude and orbit control engine to be tested installed on the adapter with the attitude and orbit control engine simulation shell, and connect the cold air test system and the simulation shell through a hose; select the corresponding plume baffle according to the output force value of the attitude control nozzle of the simulation shell, install the plume baffle device, make the plume baffle and one attitude control nozzle of the simulation shell facing coaxial and adjust the distance L, and close the remaining attitude control nozzles; Step 2: calibrate the dynamic indirect force sensor to establish the corresponding relationship between the attitude control nozzle thrust and the impact force on the plume baffle; Step 2.1: Divide the maximum thrust value of the dynamic indirect force sensor to be calibrated into i steps at equal intervals, which are used as the preset thrust input value during calibration, denoted as X i , where i = 1, 2, ~ k, i is the i-th calibration point, k is the number of calibration points; Step 2.2, controlling the cold air test system so that the thrust of the gas flow rate ejected from a single attitude control nozzle on the multi-component force measuring assembly reaches a preset thrust value X1; At this time, the indirect force sensor measures the thrust Y on the plume baffle: c11 The measured data are transmitted to the data acquisition system of the multi-component thrust vector test system, and the host computer of the multi-component thrust vector test system analyzes and processes the collected data to establish the X1 and Y c11 The corresponding relationship; Step 2.3: Follow the steps in step 2.2 to make the thrust of the single attitude control nozzle reach the preset thrust values ​​X1, X2, X3, and X4 in the ascending order of the forward direction. k The thrust on the plume baffle measured by the dynamic indirect force sensor is Y c11 , Y c21 , Y c31 ,~Y ck1 , establish X1, X2, X3, ~X k With Y c11 , Y c21 , Y c31 ,~Y ck1 One-to-one correspondence; Y ci1 is the thrust measured by the dynamic indirect force sensor at the i-th calibration point during the first positive ascending calibration stroke, i = 1, 2, ~ k; Then, the thrust of the single attitude control nozzle is calibrated in reverse descending order to reach the preset thrust value X k , ~X3, X2, X1, the thrust of the plume baffle measured by the dynamic indirect force sensor is Y fk1 ,~Y f31 , Y f21 , Y f11 , establish X1, X2, X3, ~X k With Y fk1 ,~Y f31 , Y f21 , Y f11 One-to-one correspondence; Y fi1 is the thrust measured by the dynamic indirect force sensor at the i-th calibration point during the first reverse descending stroke, i = 1, 2, ~ k; Step 2.4, repeat step 2.3, repeat the forward ascending stroke calibration and the reverse descending stroke calibration R times, and obtain multiple sets of test data Y of dynamic indirect force sensors at each calibration point cij and Y fij , where j is the number of forward and reverse strokes, j = 1, 2, ~ R; Step 2.5, calculate the average and total average of the forward and reverse travel calibration data of each calibration point according to the following formula: Where: is the average value of the forward travel calibration data of the i-th calibration point; Y cij is the jth forward travel calibration data at the i-th calibration point; is the average value of the reverse travel calibration data of the i-th calibration point; Y fij is the jth reverse stroke calibration data at the i-th calibration point; is the total average value of all calibration data of the i-th calibration point; according to Data connection, forming a calibration curve of the dynamic indirect force sensor, and establishing the full range correspondence between the dynamic indirect force sensor and the multi-component force measurement assembly; Step 3, measure the thrust output by the attitude control nozzle when the attitude and orbit control engine is working; remove the simulation shell, install the attitude and orbit control engine to be measured, align one attitude control nozzle coaxially with the plume baffle, ignite the attitude and orbit control engine, at this time, the thrust output by the attitude control nozzle when the attitude and orbit control engine is working can be measured by the dynamic indirect force sensor.

8. A method according to claim 7, characterized in that: After the step 2.5 is completed, a working straight line is established to replace the calibration curve of step 2.5, reflecting the relationship between the thrust measured by the dynamic indirect force sensor and the multi-component force measurement assembly, which is expressed as: Y= a+bX (7) Where: Y is the thrust value measured by the dynamic indirect force sensor, X is the thrust value measured by the multi-component force measuring assembly, a is the intercept of the working line on the Y axis, b is the slope of the working line, The working straight line is determined using the least squares method based on the calibration data collected in step 2.

4.

9. A method according to claim 8, characterized in that: The number of the calibration points is five, k=5.

10. A method according to claim 8, characterized in that: The specifications of the attitude control nozzle of the attitude and orbit control engine to be tested replaced in step 3 are the same as the specifications of the attitude control nozzle of the simulation shell.

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