Single-plane three-component test device and method for solid rocket engine

Abstract

The invention relates to a solid rocket engine single-plane three-component test device and method, and belongs to the technical field of solid rocket engine tests and tests. The testing device comprises a supporting assembly, a rotating assembly, a movable connecting piece, a plurality of force measuring assemblies and a limiting assembly, and according to the testing method, a single-plane three-component force testing mechanical model is constructed, and a basis is provided for data calculation; before an ignition test, the limiting assembly is loosened, so that the rotating assembly is in a free state, and the rotating assembly is connected with the supporting assembly only through the force measuring assemblies; after the ignition test, data calculation is carried out according to the torque ratio of the test device. According to the invention, the data decoupling difficulty of the six-component measurement model can be reduced.

Description

Technical Field

[0001] The present application relates to the field of solid rocket engine testing and measurement technology, and in particular to a single-plane three-force testing device and method for a solid rocket engine. Background Art

[0002] Solid rocket propulsion technology is widely used in space science experiments and national defense construction. Among them, the precise control of the thrust of solid rocket engines is of great significance for controlling the operating attitude of the aircraft and improving the target hit longitude.

[0003] Solid rocket engine test and testing technology is an important part of solid rocket propulsion technology. The lateral force of solid rocket engines is an important parameter that needs to be measured in solid rocket engine test and testing. At present, the six-component force model is mainly used, that is, the six-component force test bench is used to measure the lateral force of solid rocket engines, but there are the following problems:

[0004] First, the six-component force model has more force coupling in all directions, making data decoupling more difficult;

[0005] Secondly, the use of the six-component force model will affect the installation efficiency during the test run.

[0006] Therefore, it is necessary to propose a solution to improve one or more problems existing in the above-mentioned related technical solutions.

[0007] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0008] A first aspect of an embodiment of the present application provides a single-plane three-force test device for a solid rocket engine, comprising:

[0009] A support assembly, the support assembly comprising a bottom plate, and a pair of opposite single-body support columns and a pair of opposite double-body support columns arranged on the bottom plate, the center point of the central axis between the two single-body support columns and the center point of the central axis between the two double-body support columns coincide with each other and are projected onto a point on the bottom plate, and the point is defined as a projection point;

[0010] A rotating assembly, the lower end of which is connected to the bottom plate;

[0011] A movable connecting member, the lower end of which is connected to the upper end of the rotating assembly, and the upper end of the movable assembly is used to connect to the engine;

[0012] A plurality of force measuring assemblies, the upper end of at least one of the double-body support columns and the upper end of at least one of the single-body support columns are respectively connected to the force measuring assemblies, and the other ends of all the force measuring assemblies are respectively connected to the movable connecting members;

[0013] A limit assembly, wherein the lower end of the limit assembly is connected to the bottom plate, and the upper end of the limit assembly is connected to the movable connecting member;

[0014] Among them, any two adjacent single-body support columns and double-body support columns are connected by a first support beam; the projection of the center point of the rotating assembly and the projection of the center point of the movable connecting member both coincide with the projection point.

[0015] In an exemplary embodiment of the present application, the double-body support column comprises: two single-body support columns connected to each other, and the two single-body support columns are connected by a second support beam.

[0016] In an exemplary embodiment of the present application, a plurality of reinforcing ribs are evenly distributed on the bottom plate.

[0017] In an exemplary embodiment of the present application, the rotating assembly includes:

[0018] A bearing seat, wherein a first groove is arranged at the center of the upper end surface of the bearing seat, and the lower end of the bearing seat is connected to the bottom plate;

[0019] A bearing end cover, wherein the bearing end cover is arranged at the upper end of the bearing seat and is provided with an end cover center hole;

[0020] A thrust spherical bearing, wherein the thrust spherical bearing is fixedly arranged at two bottom groove corners of the first groove and two top groove corners formed by the first groove and the bearing end cover respectively;

[0021] A main shaft, one end of which is arranged in the first groove and clamped between the four thrust spherical bearings; the other end of the main shaft is exposed outside the center hole of the end cover, and a second groove is arranged at the center position of the end surface of the other end of the main shaft;

[0022] A first flange, one end of which is disposed in the second groove, and the other end of which is connected to the movable connecting member.

[0023] In an exemplary embodiment of the present application, each of the thrust spherical bearings comprises:

[0024] A fixed joint, one end of which is fixedly connected to the bottom groove angle or the top groove angle;

[0025] An active joint, one end of which is movably connected to the other end of the fixed joint, and the other end of the active joint is connected to the main shaft.

[0026] In an exemplary embodiment of the present application, the movable connecting member includes:

[0027] An upper flange, wherein a plurality of first connecting holes are arranged at equal intervals on the lower end surface of the upper flange;

[0028] A plurality of connecting posts, one end of each of which is correspondingly inserted into the first connecting hole; a fastening ring is arranged on the outer side of all the connecting posts, and each of the connecting posts is fixedly connected to the fastening ring;

[0029] A lower flange, wherein a plurality of second connection holes corresponding to the first connection holes are arranged at equal intervals on the upper end surface of the lower flange, and the other end of each of the connection columns is correspondingly inserted into the second connection holes; the lower flange is fixedly connected to the first flange;

[0030] Wherein, the upper flange and the lower flange have coaxial center holes.

[0031] In an exemplary embodiment of the present application, the force measuring assembly includes: a loose flange, a first adjusting member, a push-pull sensor, a second adjusting member, a flexible member, a third adjusting member, and a second flange, which are connected in sequence;

[0032] Wherein, one end of the loose flange is fixedly connected to the upper end of the single support column, and the other end of the loose flange is connected to the first adjusting member;

[0033] One end of the second flange is connected to the third adjusting member, and the other end of the second flange is fixedly connected to the side surface of the upper flange.

[0034] In an exemplary embodiment of the present application, the limiting assembly includes:

[0035] A limiting rod, the bottom end of which is arranged on the bottom plate, and the upper end of which is connected to the upper flange;

[0036] A plurality of locking assemblies, wherein the limiting rod is sequentially sleeved with a plurality of locking assemblies from top to bottom, and each locking assembly comprises a collar, a locking nut and a spare nut which are sequentially connected.

[0037] A second aspect of the embodiment of the present application provides a single-plane three-force test method for a solid rocket engine, comprising the following steps:

[0038] Connecting a solid rocket motor to a movable connection member in the test device;

[0039] Calibrate the push-pull sensor, and install the calibrated push-pull sensor in the force measuring assembly;

[0040] Install the loose flange in the force measuring assembly on the upper end of the double-body support column or the upper end of the single-body support column, and fix it to the movable connecting piece;

[0041] A single-plane three-force test mechanical model is constructed with the rotation center of the main shaft in the rotating assembly as the center of the circle, the central axis between the two double-body support columns as the x-axis, and the central axis between the two single-body support columns as the y-axis; before the ignition test, the limit assembly is loosened to put the rotating assembly in a free state, and according to the single-plane three-force test mechanical model, the force measuring assembly is used to measure data of the solid rocket engine;

[0042] After the ignition test, the measured data is resolved according to the torque ratio of the test device.

[0043] In an exemplary embodiment of the present application, the expression of the single-plane three-force test mechanical model is:

[0044]

[0045] Wherein, F represents the final force, and the angle between the direction of the final force F and the x-axis is θ. F x represents the actual thrust in the x-axis direction, F y represents the actual thrust in the y-axis direction, L1 represents the distance from the nozzle axis of the engine to the rotation center, L2 represents the distance from the force measuring assembly to the rotation center, f1 represents the measurement value of the first push-pull sensor, f2 represents the measurement value of the second push-pull sensor, and f3 represents the measurement value of the third push-pull sensor.

[0046] Beneficial effects:

[0047] The present application provides a single-plane three-force test device and method for a solid rocket engine, which has at least the following beneficial effects:

[0048] (1) This application provides the theoretical feasibility of this method by designing and constructing a single-plane three-force test mechanical model;

[0049] (2) The single-plane three-force test device designed in the present application includes a support assembly, a rotating assembly, a movable connection, multiple force measuring assemblies and a limit assembly that are reasonably connected. Before the ignition test, the limit assembly is loosened to put the rotating assembly in a free state, thereby ensuring the reliability of the test data. The single-plane three-force test mechanical model is used to test and decouple the test data, thereby ensuring the accuracy of the test data and reducing the difficulty of data decoupling. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] The drawings herein are incorporated into the specification and constitute a part of the specification, illustrate embodiments consistent with the present application, and together with the specification are used to explain the principles of the present application. Obviously, the drawings described below are only some embodiments of the present application, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0051] Figure 1 A schematic structural diagram of a single-plane three-force test device for a solid rocket engine proposed in a first aspect of an exemplary embodiment of the present application is shown;

[0052] Figure 2 A top view of a support assembly in an exemplary embodiment of the present application is shown;

[0053] Figure 3a A schematic diagram showing a single-body support column and a double-body support column when the support assembly is in one direction in an exemplary embodiment of the present application;

[0054] Figure 3b A schematic diagram showing a single-body support column and a double-body support column when the support assembly is in another direction in an exemplary embodiment of the present application;

[0055] Figure 4 A schematic diagram showing the structure of a rotating assembly in an exemplary embodiment of the present application is shown;

[0056] Figure 5 A schematic diagram showing the structure of an active connection member in an exemplary embodiment of the present application is shown;

[0057] Figure 6 A schematic structural diagram of a force measuring assembly in an exemplary embodiment of the present application is shown;

[0058] Figure 7 A schematic diagram showing the structure of a limit assembly in an exemplary embodiment of the present application is shown;

[0059] Figure 8 A schematic diagram showing the connection relationship of the limit assembly in the single-plane three-force test device in the exemplary embodiment of the present application;

[0060] Fig. 9A schematic diagram showing the steps of a single-plane three-force test method for a solid rocket engine proposed in the second aspect of the exemplary embodiment of the present application.

[0061] In the figure, 100, single-plane three-force test device; 110, support assembly; 111, bottom plate; 1111, reinforcing rib; 112, single-body support column; 113, double-body support column; 114, projection point; 115, first support beam; 116, second support beam; 120, rotating assembly; 121, bearing seat; 1211, first groove; 122, bearing end cover; 1221, end cover center hole; 123, thrust joint bearing; 1231, fixed joint; 1232, movable joint; 124, main shaft; 1241, second groove; 125 , first flange; 130, movable connection; 131, upper flange; 1311, coaxial center hole; 132, connecting column; 133, lower flange; 134, fastening ring; 140, force measuring assembly; 141, loose flange; 142, first adjusting member; 143, push-pull sensor; 144, second adjusting member; 145, flexible member; 146, third adjusting member; 147, second flange; 150, limit assembly; 151, limit rod; 152, locking assembly; 1521, collar; 1522, locking nut; 1523, spare nut. DETAILED DESCRIPTION

[0062] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in a variety of forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this application will be more comprehensive and complete and fully convey the concepts of the example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0063] In addition, the accompanying drawings are only schematic illustrations of the present application and are not necessarily drawn to scale. The same reference numerals in the figures represent the same or similar parts, and thus their repeated description will be omitted. Some of the block diagrams shown in the accompanying drawings are functional entities and do not necessarily correspond to physically or logically independent entities. These functional entities can be implemented in software form, or implemented in one or more hardware modules or integrated circuits, or implemented in different networks and / or processor devices and / or microcontroller devices.

[0064] With the emergence of multi-directional multi-nozzle rocket engines, the measurement of lateral force has become a key and difficult technology for ground test driving. In the past, multi-component force measurements were mostly dual-plane three-dimensional six-component force tests, with more coupling forces in each direction, making data decoupling more difficult. In order to solve the above technical problems, the first aspect of this exemplary embodiment provides a single-plane three-component force test device 100 for a solid rocket engine, such as Figure 1 As shown, including:

[0065] A support assembly 110, the support assembly 110 includes a bottom plate 111, and a pair of opposite single-body support columns 112 and a pair of opposite double-body support columns 113 disposed on the bottom plate 111, the center point of the central axis between the two single-body support columns 112 and the center point of the central axis between the two double-body support columns 113 coincide with each other and are projected onto a point on the bottom plate 111, and the point is defined as a projection point 114;

[0066] A rotating assembly 120, the lower end of which is connected to the bottom plate 111;

[0067] A movable connecting member 130, wherein the lower end of the movable connecting member 130 is connected to the upper end of the rotating assembly 120, and the upper end of the movable connecting member 130 is used to be connected to the engine;

[0068] A plurality of force measuring assemblies 140, the upper end of at least one double-body support column 113, and the upper end of at least one single-body support column 112 are respectively connected to the force measuring assemblies 140, and the other ends of all the force measuring assemblies 140 are respectively connected to the movable connecting member 130;

[0069] A limiting assembly 150, wherein the lower end of the limiting assembly 150 is connected to the bottom plate 111, and the upper end of the limiting assembly 150 is connected to the movable connecting member 130;

[0070] Any two adjacent single support columns 112 and double support columns 113 are connected by a first support beam 115; the center point of the rotating assembly 120 and the center point of the movable connecting member 130 both coincide with the projection point 114.

[0071] A second aspect of this exemplary embodiment provides a single-plane three-force test method for a solid rocket engine, which may include the following steps:

[0072] Step S101: Connect the solid rocket engine to the movable connecting piece in the test device.

[0073] Step S102: construct a single-plane three-force test mechanical model with the rotation center of the main shaft in the rotating assembly as the center of the circle, the central axis between the two double-body support columns as the x-axis, and the central axis between the two single-body support columns as the y-axis.

[0074] Step S103: Before the ignition test, the limit assembly is loosened to put the rotating assembly in a free state, and the solid rocket engine is measured using the force measuring assembly according to the single-plane three-force test mechanical model.

[0075] Step S104: After the ignition test, the measurement data is solved according to the torque ratio of the test device.

[0076] The present application embodiment provides a solid rocket engine single-plane three-force test device and method, which has at least the following beneficial effects:

[0077] (1) This application provides the theoretical feasibility of this method by designing and constructing a single-plane three-force test mechanical model;

[0078] (2) The single-plane three-force test device 100 designed in the present application includes a support assembly 110, a rotating assembly 120, a movable connection 130, a plurality of force measuring assemblies 140 and a limit assembly 150 that are reasonably connected. Before the ignition test, the limit assembly 150 is released to put the rotating assembly 120 in a free state, thereby ensuring the reliability of the test data. The single-plane three-force test mechanical model is used to test and decouple the test data, thereby ensuring the accuracy of the test data and reducing the difficulty of data decoupling.

[0079] Below, a solid rocket engine single-plane three-force test device 100 and method proposed in this example embodiment will be described in more detail.

[0080] A first aspect of this example embodiment provides a solid rocket engine single-plane three-dimensional force test device 100.

[0081] In one embodiment, by Figure 2 It can be seen that the bottom plate 111 can be designed into various regular shapes, such as circular, rectangular, polygonal and other shapes. In this embodiment, the bottom plate 111 is designed as an octagonal structure and includes four pairs of parallel sides. It can be seen that two pairs of reinforcing ribs 1111 are evenly arranged on the octagonal bottom plate 111, each pair of reinforcing ribs 1111 includes two mutually parallel reinforcing ribs 1111, and one pair of reinforcing ribs 1111 is vertically crossed with the other pair of reinforcing ribs 1111 to form a cross-shaped layout. Such a design divides the bottom plate 111 into multiple partitions, and the middle rectangular partition is used to install the rotating assembly 120, wherein a pair of single-body support columns 112 are arranged between a pair of reinforcing ribs 1111, and a pair of double-body support columns 113 are arranged between the other pair of reinforcing ribs 1111.

[0082] The bottom plate 111 is arranged in a regular pattern and the reinforcing ribs 1111 are evenly arranged. On the one hand, it is helpful to ensure that the bottom plate 111 and the single support column 112 and the double support column 113 arranged thereon are evenly stressed during the single-plane three-force test; on the other hand, the reinforcing ribs 1111 increase the rigidity and strength of the bottom plate 111. Figure 2 It can also be seen that the positions of the paired reinforcing ribs 1111 are just close to the lower ends of both sides of the single-body support column 112 and the double-body support column 113, so as to fasten and support the single-body support column 112 and the double-body support column 113.

[0083] Furthermore, in this embodiment, the double support column 113 includes two fixedly connected single support columns 112. Any two adjacent single support columns 112 and the double support column 113 are connected by a first support beam 115; the two single support columns 112 are connected by a second support beam 116, thereby designing an overall stable support assembly 110.

[0084] Further, by Figure 3a and Figure 3b The design positions of the single support column 112 and the double support column 113 can be seen from different angles and directions. The bottom plate 111 is integrally welded with the single support column 112 and the double support column 113. During the single-plane three-force test, the bottom plate 111 with the reinforcing ribs 1111 is fixed to the ground, thereby ensuring the safety and stability of the single-plane three-force test.

[0085] In one embodiment, by Figure 4 As shown, in this embodiment, the rotating assembly 120 includes:

[0086] The bearing seat 121 has a first groove 1211 at the center of the upper end surface of the bearing seat 121 , and the lower end of the bearing seat 121 is connected to the bottom plate 111 ; in this embodiment, the bearing seat 121 and the bottom plate 111 are connected by bolts.

[0087] The bearing end cover 122 is arranged at the upper end of the bearing seat 121, and the bearing end cover 122 is provided with an end cover center hole 1221;

[0088] The thrust spherical bearing 123 is fixedly provided at two bottom groove corners of the first groove 1211 and two top groove corners formed by the first groove 1211 and the bearing end cover 122;

[0089] A main shaft 124, one end of which is disposed in the first groove 1211 and clamped between the four thrust spherical bearings 123; the other end of the main shaft 124 is exposed outside the end cover center hole 1221, and a second groove 1241 is disposed at the center position of the end surface of the other end of the main shaft 124;

[0090] The first flange 125, one end of which is disposed in the second groove 1241, and the other end of which is connected to the movable connecting member 130. In this embodiment, the first flange 125 and the movable connecting member 130 are connected by bolts. It can be seen that the projection of the center point of the bearing seat 121, the projection of the center point of the bearing end cover 122, and the projection of the center point of the main shaft 124 all coincide with the projection point 114.

[0091] Furthermore, the setting of the thrust spherical bearing 123 provides a degree of freedom for the rotating assembly 120, and the rotation center of the main shaft 124 is located at the spherical center of the thrust spherical bearing 123. Therefore, the design of the rotating assembly 120 can be used to perform thrust testing, calculate the difference in force arm, and obtain the coefficient between the thrust test value and the actual value, thereby ensuring the accuracy of the thrust test.

[0092] Furthermore, each thrust spherical bearing 123 includes:

[0093] A fixed joint 1231, one end of which is fixedly connected to the bottom groove angle or the top groove angle;

[0094] The movable joint 1232 has one end movably connected to the other end of the fixed joint 1231 , and the other end of the movable joint 1232 is connected to the main shaft 124 .

[0095] In one embodiment, by Figure 5 As shown, in this embodiment, the movable connecting member 130 includes:

[0096] An upper flange 131, a plurality of first connection holes are arranged at equal intervals on the lower end surface of the upper flange 131;

[0097] A plurality of connecting posts 132, one end of each connecting post 132 is correspondingly inserted into the first connecting hole; a fastening ring 134 is provided on the outer side of all the connecting posts 132, and each connecting post 132 is fixedly connected to the fastening ring 134;

[0098] A lower flange 133, wherein a plurality of second connection holes corresponding to the first connection holes are arranged at equal intervals on the upper end surface of the lower flange 133, and the other end of each connection column is inserted into the second connection hole respectively; the lower flange 133 is fixedly connected to the first flange 125;

[0099] The upper flange 131 and the lower flange 133 have coaxial center holes 1311 .

[0100] Furthermore, the movable connection 130 is directly connected to the solid rocket motor, and when the motor is ignited, thrust testing is performed through the degrees of freedom provided by the rotating assembly 120.

[0101] In one embodiment, by Figure 6 As shown, in this embodiment, the force measuring assembly 140 includes: a loose flange 141, a first adjusting member 142, a push-pull sensor 143, a second adjusting member 144, a flexible member 145, a third adjusting member 146 and a second flange 147 connected in sequence;

[0102] One end of the loose flange 141 is fixedly connected to the upper end of the single support column 112, and the other end of the loose flange 141 is connected to the first adjustment member 142;

[0103] One end of the second flange 147 is connected to the third adjusting member 146 , and the other end of the second flange 147 is fixedly connected to the side surface of the upper flange 131 .

[0104] Furthermore, the force measuring assembly 140 adopts a structure in which a push-pull sensor 143 is matched with a flexible member 145, which can effectively test the lateral force and eliminate the influence of the remaining thrust on the push-pull sensor 143. At the same time, the three adjustment members are provided so that the length of the entire force measuring assembly 140 can be adjusted, which is convenient for installation. In this embodiment, the three adjustment members can all choose to use a matching method of an adjustment nut and an adjustment screw to adjust the length of the force measuring assembly 140.

[0105] Furthermore, in the present embodiment, three force measuring assemblies 140 are installed on the force measuring plane, namely, one is installed on the upper end of the single-body support column 112, and the other two are installed on the upper end of an adjacent double-body support column 113. Thus, the overall roll caused by the thrust of the solid rocket engine can be eliminated while measuring the force, thereby ensuring the reliability of the single-plane three-force test.

[0106] In one embodiment, by Figure 7 and Figure 8 As shown, in this embodiment, the limiting assembly 150 includes:

[0107] A limiting rod 151, the bottom end of which is disposed on the bottom plate 111, and the upper end of which is connected to the upper flange 131;

[0108] Multiple locking assemblies 152, the limiting rod 151 is sequentially sleeved with multiple locking assemblies 152 from top to bottom, and each locking assembly 152 includes a collar 1521, a locking nut 1522 and a spare nut 1523 connected in sequence. In this embodiment, two locking assemblies 152 are arranged on the limiting rod 151. After the collar 1521 is sleeved on the limiting rod 151, the locking nut 1522 is twisted, and the upper and lower locking assemblies 152 are used to keep the entire single-plane three-body test device 100 in a fixed state.

[0109] Furthermore, the limiting assembly 150 is connected to the bottom plate 111 through the limiting rod 151, and is pressed up and down by using the locking nut 1522 and the lower flange 133 of the movable connecting member 130. When the single-plane three-force test is in the preparation state, the locking nut 1522 is twisted and locked up and down; when the solid rocket engine is installed and the preliminary preparation work is completed, the locking nut 1522 is loosened up and down, and the solid rocket engine is in the test state.

[0110] The second aspect of this example embodiment provides a single-plane three-force test method for a solid rocket engine.

[0111] The whole workflow of single-plane three-force test using single-plane three-force test device is as follows: Fig. 9 As shown, the following steps may be included:

[0112] Step S101: Connecting the solid rocket engine to the movable connecting piece in the test device.

[0113] Step S102: calibrate the push-pull sensor, and install the calibrated push-pull sensor in the force measuring assembly.

[0114] Step S103: Install the loose flange in the force measuring assembly on the upper end of the double-body support column or the upper end of the single-body support column, and fix the loose flange to the movable connecting piece.

[0115] Step S104: construct a single-plane three-force test mechanical model with the rotation center of the main shaft in the rotating assembly as the center of the circle, the central axis between the two double-body support columns as the x-axis, and the central axis between the two single-body support columns as the y-axis.

[0116] The expression of the single-plane three-force test mechanical model is:

[0117]

[0118] Wherein, F represents the final force, and the angle between the direction of the final force F and the x-axis is θ. F x represents the actual thrust in the x-axis direction, F y represents the actual thrust in the y-axis direction, L1 represents the distance from the nozzle axis of the engine to the rotation center, L2 represents the distance from the force measuring assembly to the rotation center, f1 represents the measurement value of the first push-pull sensor, f2 represents the measurement value of the second push-pull sensor, and f3 represents the measurement value of the third push-pull sensor.

[0119] Step S105: Before the ignition test, loosen the limit assembly to put the rotating assembly in a free state, and use the force measuring assembly to measure the data of the solid rocket engine according to the single-plane three-force test mechanical model.

[0120] Step S106: After the ignition test, the measurement data is solved according to the torque ratio of the test device.

[0121] The present application proposes a single-plane three-force test device and method for a solid rocket engine, which can be used for lateral force testing of multi-directional multi-nozzle solid rocket engines, and is particularly suitable for working conditions where the nozzle axis is perpendicular to the axis of the solid rocket engine. If there is an angle between the nozzle axis of the solid rocket engine and the axis of the engine, then there is a main thrust on the axis of the engine. In this way, a push-pull sensor can be added to the rotating assembly to test the main thrust, expanding the three-force test device into a four-force test device. The present application can reduce the difficulty of traditional six-component force decoupling through two force measuring planes.

[0122] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the embodiments of the present application, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0123] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification.

[0124] The above description is only a specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or substitutions within the technical scope disclosed in the present application, and these modifications or substitutions should be included in the protection scope of the present invention.

[0125] Those skilled in the art will readily appreciate other embodiments of the present application after considering the specification and practicing the invention disclosed herein. The present application is intended to cover any modification, use or adaptation of the present application, which follows the general principles of the present application and includes common knowledge or customary technical means in the art that are not disclosed in the present application.

Claims

1. A single-plane three-force test device for a solid rocket engine, characterized in that: include: A support assembly, the support assembly comprising a bottom plate, and a pair of opposite single-body support columns and a pair of opposite double-body support columns arranged on the bottom plate, the center point of the central axis between the two single-body support columns and the center point of the central axis between the two double-body support columns coincide with each other and are projected onto a point on the bottom plate, and the point is defined as a projection point; A rotating assembly, the lower end of which is connected to the bottom plate; A movable connecting member, the lower end of which is connected to the upper end of the rotating assembly, and the upper end of which is used to be connected to the engine; A plurality of force measuring assemblies, the upper end of at least one of the double-body support columns and the upper end of at least one of the single-body support columns are respectively connected to the force measuring assemblies, and the other ends of all the force measuring assemblies are respectively connected to the movable connecting members; A limit assembly, wherein the lower end of the limit assembly is connected to the bottom plate, and the upper end of the limit assembly is connected to the movable connecting member; Among them, any two adjacent single-body support columns and double-body support columns are connected by a first support beam; the projection of the center point of the rotating assembly and the projection of the center point of the movable connecting member both coincide with the projection point.

2. The single-plane three-force test device for solid rocket engines according to claim 1, characterized in that: The double-body support column comprises: two single-body support columns connected to each other, and the two single-body support columns are connected via a second support beam.

3. The single-plane three-force test device for solid rocket engines according to claim 2, characterized in that: A plurality of reinforcing ribs are evenly arranged on the bottom plate.

4. The single-plane three-force test device for solid rocket engines according to claim 2, characterized in that: The rotating assembly comprises: A bearing seat, wherein a first groove is arranged at the center of the upper end surface of the bearing seat, the lower end of the bearing seat is connected to the bottom plate, and the center point of the lower end of the bearing seat; A bearing end cover, wherein the bearing end cover is arranged at the upper end of the bearing seat and is provided with an end cover center hole; A thrust spherical bearing, wherein the thrust spherical bearing is fixedly arranged at two bottom groove corners of the first groove and two top groove corners formed by the first groove and the bearing end cover respectively; A main shaft, one end of which is arranged in the first groove and clamped between the four thrust spherical bearings; the other end of the main shaft is exposed outside the center hole of the end cover, and a second groove is arranged at the center position of the end surface of the other end of the main shaft; A first flange, one end of which is disposed in the second groove, and the other end of which is connected to the movable connecting member.

5. The single-plane three-force test device for solid rocket engines according to claim 4, characterized in that: Each of the thrust spherical bearings comprises: A fixed joint, one end of which is fixedly connected to the bottom groove angle or the top groove angle; An active joint, one end of which is movably connected to the other end of the fixed joint, and the other end of the active joint is connected to the main shaft.

6. The single-plane three-force test device for solid rocket engines according to claim 4, characterized in that: The movable connecting member comprises: An upper flange, a coaxial center hole, and a plurality of first connection holes are arranged at equal intervals on the lower end surface of the upper flange; A plurality of connecting posts, one end of each of which is correspondingly inserted into the first connecting hole; a fastening ring is arranged on the outer side of all the connecting posts, and each of the connecting posts is fixedly connected to the fastening ring; A lower flange, wherein a plurality of second connection holes corresponding to the first connection holes are arranged at equal intervals on the upper end surface of the lower flange, and the other end of each of the connection columns is correspondingly inserted into the second connection holes; the lower flange is fixedly connected to the first flange; Wherein, the upper flange and the lower flange have coaxial center holes.

7. The single-plane three-force test device for solid rocket engines according to claim 6, characterized in that: The force measuring assembly comprises: a loose flange, a first adjusting member, a push-pull sensor, a second adjusting member, a flexible member, a third adjusting member and a second flange, which are connected in sequence; Wherein, one end of the loose flange is fixedly connected to the upper end of the single support column, and the other end of the loose flange is connected to the first adjusting member; One end of the second flange is connected to the third adjusting member, and the other end of the second flange is fixedly connected to the side surface of the upper flange.

8. The single-plane three-force test device for solid rocket engines according to claim 7, characterized in that: The limiting component comprises: A limiting rod, the bottom end of which is arranged on the bottom plate, and the upper end of which is connected to the upper flange; A plurality of locking assemblies, wherein the limiting rod is sequentially sleeved with a plurality of locking assemblies from top to bottom, and each locking assembly comprises a collar, a locking nut and a spare nut which are sequentially connected.

9. A single-plane three-force test method for a solid rocket engine, characterized in that: The three-force test method is carried out using the test device according to any one of claims 1 to 8, and the test method comprises the following steps: Connecting a solid rocket motor to a movable connection member in the test device; Calibrate the push-pull sensor, and install the calibrated push-pull sensor in the force measuring assembly; Installing the loose flange in the force measuring assembly on the upper end of the double-body support column or the upper end of the single-body support column, and fixing the loose flange with the movable connecting piece; A single-plane three-force test mechanical model is constructed with the rotation center of the main shaft in the rotating assembly as the center of the circle, the central axis between the two double-body support columns as the x-axis, and the central axis between the two single-body support columns as the y-axis; before the ignition test, the limit assembly is loosened to put the rotating assembly in a free state, and according to the single-plane three-force test mechanical model, the force measuring assembly is used to measure data of the solid rocket engine; After the ignition test, the measured data is resolved according to the torque ratio of the test device.

10. The single-plane three-force test method for solid rocket engines according to claim 9, characterized in that: The expression of the single-plane three-force test mechanical model is: Wherein, F represents the final force, and the angle between the direction of the final force F and the x-axis is θ. F x represents the actual thrust in the x-axis direction, F y represents the actual thrust in the y-axis direction, L1 represents the distance from the nozzle axis of the engine to the rotation center, L2 represents the distance from the force measuring assembly to the rotation center, f1 represents the measurement value of the first push-pull sensor, f2 represents the measurement value of the second push-pull sensor, and f3 represents the measurement value of the third push-pull sensor.

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