Solid rocket engine single-plane three-component force test device and method

Abstract

The application relates to a single-plane three-component force test device and method of a solid rocket engine, and belongs to the technical field of solid rocket engine testing and testing. The test device comprises a support assembly, a rotating assembly, a movable connecting piece, a plurality of force measuring assemblies and a limiting assembly. The test method provides a basis for data calculation by constructing a single-plane three-component force test mechanical model. Before ignition test, the limiting assembly is loosened, the rotating assembly is in a free state, and the plurality of force measuring assemblies are connected with the support assembly. After ignition test, data calculation is carried out according to the moment ratio of the test device. The application can reduce the data decoupling difficulty of the six-component force measurement model.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of solid rocket engine test and test technology, and particularly relates to a single-plane three-component force test device and method for a solid rocket engine. BACKGROUND

[0002] Solid rocket propulsion technology is widely used in space science experiments and national defense construction, and accurate control of the thrust of a solid rocket engine is of great significance to control the running attitude of a spacecraft and improve target hitting longitude.

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

[0004] Firstly, the forces in each direction of the six-component force model are coupled, and data decoupling is difficult;

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

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

[0007] It should be noted that the information disclosed in the above background section is only used to strengthen the understanding of the background of the present application, and therefore can include information that does not constitute prior art known to those of ordinary skill in the art. SUMMARY

[0008] The first aspect of the embodiment of the present application provides a single-plane three-component 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 support columns and a pair of opposite double support columns arranged on the bottom plate, the center points of the central axes between the two single support columns and the center points of the central axes between the two double support columns coincide, and a point projected on the bottom plate is defined as a projection point;

[0010] a rotating assembly, the lower end of the rotating assembly being connected with the bottom plate;

[0011] a movable connecting piece, the lower end of the movable connecting piece being connected with the upper end of the rotating assembly, and the upper end of the movable assembly being used for connecting with an engine;

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

[0013] A limiting assembly, a lower end of the limiting assembly is connected to the bottom plate, and an upper end of the limiting assembly is connected to the movable connecting piece;

[0014] Wherein, any two adjacent single-body support columns and double-body support columns are connected through 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 piece both coincide with the projection point.

[0015] In an example 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 through a second support beam.

[0016] In an example embodiment of the present application, a plurality of reinforcing ribs are uniformly arranged on the bottom plate.

[0017] In an example embodiment of the present application, the rotating assembly comprises:

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

[0019] A bearing end cover, the bearing end cover is arranged at the upper end of the bearing seat, and a center hole is arranged on the bearing end cover;

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

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

[0022] A first flange plate, one end of the first flange plate is arranged in the second recess, and the other end of the first flange plate is connected to the movable connecting piece.

[0023] In an example embodiment of the present application, each thrust joint bearing comprises:

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

[0025] A movable joint, one end of the movable joint is movably connected with the other end of the fixed joint, and the other end of the movable joint is connected with the main shaft.

[0026] In an example embodiment of the present application, the movable connecting member comprises:

[0027] An upper flange plate, a plurality of first connecting holes are equidistantly arranged on the lower end surface of the upper flange plate;

[0028] A plurality of connecting columns, one end of each of the connecting columns is respectively inserted into the first connecting hole; the outer side of all the connecting columns is provided with a fastening ring, and each of the connecting columns is fixedly connected with the fastening ring;

[0029] A lower flange plate, a plurality of second connecting holes corresponding to the first connecting holes are equidistantly arranged on the upper end surface of the lower flange plate, and the other end of each of the connecting columns is respectively inserted into the second connecting hole; the lower flange plate is fixedly connected with the first flange plate;

[0030] The upper flange plate and the lower flange plate have coaxial center holes.

[0031] In an example embodiment of the present application, the force measuring assembly comprises, in sequence: a loose sleeve flange, a first adjusting member, a push-pull sensor, a second adjusting member, a flexible member, a third adjusting member, and a second flange plate;

[0032] One end of the loose sleeve flange is fixedly connected with the upper end of the single support column, and the other end of the loose sleeve flange is connected with the first adjusting member.

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

[0034] In an example embodiment of the present application, the limiting assembly comprises:

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

[0036] A plurality of locking assemblies, a plurality of locking assemblies are sequentially sleeved on the limiting rod from top to bottom, and each locking assembly comprises, in sequence, a sleeve ring, a locking nut, and a spare nut.

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

[0038] The solid rocket engine is connected with the movable connecting 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 sleeve flange plate 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 fixedly connect with the movable connecting piece;

[0041] Construct a single-plane three-component force test mechanical model with the rotation center of the main shaft in the rotating assembly as the center, the middle axis between the two double-body support columns as the x-axis, and the middle axis between the two single-body support columns as the y-axis; before the ignition test, loosen the limiting assembly so that the rotating assembly is in a free state, and according to the single-plane three-component force test mechanical model, use the force measuring assembly to measure the data of the solid rocket engine;

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

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

[0044]

[0045] wherein F represents the final force, 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] Advantages:

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

[0048] (1) The present application constructs a single-plane three-component force test mechanical model, which provides the theoretical feasibility of the method;

[0049] (2) The single-plane three-component test device is designed, including a support assembly, a rotating assembly, a movable connecting piece, a plurality of force measuring assemblies and a limiting assembly connected reasonably, and before the ignition test, the limiting assembly is loosened, so that the rotating assembly is in a free state, thereby ensuring the reliability of the test data, and the single-plane three-component test mechanical model is used to test and decouple the test data, ensuring the accuracy of the test data and reducing the difficulty of data decoupling. BRIEF DESCRIPTION OF DRAWINGS

[0050] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and serve to explain the principles of the present application. It is apparent that the accompanying drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0051] Figure 1 A structure schematic diagram of a single-plane three-component test device for solid rocket engine according to the first aspect of the exemplary embodiments of the present application is shown;

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

[0053] Figure 3a A schematic diagram of the single support column and the double support column of the support assembly in one direction in the exemplary embodiments of the present application is shown;

[0054] Figure 3b A schematic diagram of the single support column and the double support column of the support assembly in another direction in the exemplary embodiments of the present application is shown;

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

[0056] Figure 5 A structure schematic diagram of the movable connecting piece in the exemplary embodiments of the present application is shown;

[0057] Figure 6 A structure schematic diagram of the force measuring assembly in the exemplary embodiments of the present application is shown;

[0058] Figure 7 A structure schematic diagram of the limiting assembly in the exemplary embodiments of the present application is shown;

[0059] Figure 8 A schematic diagram of the connection relationship of the limiting assembly in the single-plane three-component test device in the exemplary embodiments of the present application is shown;

[0060] Figure 9A step schematic diagram of a single-plane three-component force test method of a solid rocket engine according to the second aspect of the example embodiments of the present application is shown.

[0061] In the figure, 100, single-plane three-component force test device; 110, support assembly; 111, bottom plate; 1111, reinforcing rib; 112, single support column; 113, double 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 plate; 130, movable connecting piece; 131, upper flange plate; 1311, coaxial center hole; 132, connecting column; 133, lower flange plate; 134, fastening ring; 140, force measuring assembly; 141, loose sleeve flange; 142, first adjusting piece; 143, push-pull sensor; 144, second adjusting piece; 145, flexible piece; 146, third adjusting piece; 147, second flange plate; 150, limiting assembly; 151, limiting rod; 152, locking assembly; 1521, collar; 1522, locking nut; 1523, spare nut. DETAILED DESCRIPTION

[0062] Example implementations will now be described more fully with reference to the accompanying drawings. Example implementations may, however, be implemented in many different forms and should not be construed as limited to the examples set forth herein; rather, these example implementations are provided so that this disclosure will be thorough and complete, and will fully convey the scope of example implementations to those skilled in the art. Features, structures or characteristics described in conjunction with the described examples can be combined in any suitable manner in one or more implementations.

[0063] In addition, the drawings are to be considered in all respects as illustrative and not restrictive; identical reference numerals have been used, where possible, to denote identical or similar features, and thus repetition of the description thereof will be omitted. Some of the blocks in the drawings are functional blocks that do not necessarily have to be implemented with physical or logical separable entities. These functional blocks can be implemented with software, or in one or more hardware modules or integrated circuits, or in different network and / or processor devices and / or microcontroller devices.

[0064] With the emergence of multi-directional multi-nozzle rocket engines, the measurement of side force has become a key and difficult technology for ground tests. The previous multi-component force measurement is mostly double-plane three-dimensional six-component force test, and there are more coupling forces in each direction, and it is difficult to decouple the data. In order to solve the above technical problems, the first aspect of the example embodiments of the present application provides a single-plane three-component force test device 100 of a solid rocket engine, as shown inFigure 1 As shown, comprising:

[0065] A support assembly 110, the support assembly 110 includes a bottom plate 111, and a pair of opposite single support columns 112 and a pair of opposite double support columns 113 arranged on the bottom plate 111, the center points of the central axes between the two single support columns 112 and the center points of the central axes between the two double support columns 113 coincide, and a point projected on the bottom plate 111, which is defined as a projection point 114;

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

[0067] A movable connecting piece 130, the lower end of the movable connecting piece 130 is connected with the upper end of the rotating assembly 120, and the upper end of the movable connecting piece 130 is used for connecting with the engine;

[0068] A plurality of force measuring assemblies 140, the upper end of at least one double support column 113 and the upper end of at least one single support column 112 are respectively connected with the force measuring assembly 140, and the other end of all the force measuring assemblies 140 is respectively connected with the movable connecting piece 130;

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

[0070] Among them, any two adjacent single support columns 112 and double support columns 113 are connected through a first support beam 115; the center point of the rotating assembly 120 and the center point of the movable connecting piece 130 both coincide with the projection point 114

[0071] The second aspect of the example embodiment provides a single-plane three-component force test method of a solid rocket engine, which can include the following steps:

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

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

[0074] Step S103: before the ignition test, loosening the limiting assembly, making the rotating assembly in a free state, and according to the single-plane three-component test mechanics model, measuring the data of the solid rocket engine by using the force measuring assembly.

[0075] Step S104: after the ignition test, calculating the measurement data according to the torque ratio of the test device.

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

[0077] (1) The single-plane three-component force test mechanical model is constructed by the embodiment of the present application, and the method is theoretically feasible;

[0078] (2) The single-plane three-component force test device 100 is designed in the embodiment of the present application, which comprises a support assembly 110, a rotating assembly 120, a movable connecting piece 130, a plurality of force measuring assemblies 140 and a limiting assembly 150 connected reasonably, and before ignition test, the limiting assembly 150 is loosened, so that the rotating assembly 120 is in a free state, thereby ensuring the reliability of the test data, and the single-plane three-component force test mechanical model is used for testing and decoupling the test data, so that the accuracy of the test data is ensured, and the difficulty of data decoupling is reduced.

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

[0080] The first aspect of the present example embodiment provides a solid rocket engine single-plane three-component force test device 100.

[0081] In one embodiment, the single-plane three-component force test device 100 comprises a support assembly 110, a rotating assembly 120, a movable connecting piece 130, a plurality of force measuring assemblies 140 and a limiting assembly 150. Figure 2 It can be seen that the bottom plate 111 can be designed in various regular shapes, such as circular, rectangular, polygonal and various shapes. In the embodiment, the bottom plate 111 is designed as an octagonal structure, and comprises four pairs of parallel edges. It can be seen that two pairs of reinforcing ribs 1111 are uniformly arranged on the octagonal bottom plate 111, each pair of reinforcing ribs 1111 comprises two parallel reinforcing ribs 1111, and one pair of reinforcing ribs 1111 is arranged perpendicularly intersecting with the other pair of reinforcing ribs 1111, forming a cross-shaped layout. Such design divides the bottom plate 111 into multiple partitions, and the rectangular partition in the middle is used for mounting the rotating assembly 120. One pair of single-body support columns 112 is arranged between one pair of reinforcing ribs 1111, and one pair of double-body support columns 113 is arranged between the other pair of reinforcing ribs 1111.

[0082] The bottom plate 111 is arranged as a regular pattern and the reinforcing ribs 1111 are uniformly arranged, which on the one hand helps the bottom plate 111 and the single-body support columns 112 and the double-body support columns 113 arranged thereon to bear force uniformly during the single-plane three-component force test, and on the other hand, the reinforcing ribs 1111 increase the rigidity and strength of the bottom plate 111, which Figure 2 It can also be seen that the positions of the paired reinforcing ribs 1111 are just close to the lower ends of the two sides of the single-body support columns 112 and the double-body support columns 113 respectively, thereby being able to fasten and support the single-body support columns 112 and the double-body support columns 113.

[0083] Further, in the embodiment, the double-body support column 113 comprises two single-body support columns 112 fixedly connected. Any two adjacent single-body support columns 112 and double-body support columns 113 are connected through a first support beam 115; two single-body support columns 112 are connected through a second support beam 116, thereby designing a support assembly 110 stable as a whole.

[0084] Further, by Figure 3a and Figure 3b The design position of the single-body support column 112 and the double-body support column 113 can be seen from different angles and directions. The bottom plate 111 is a whole welded piece with the single-body support column 112 and the double-body support column 113. In the process of carrying out the single-plane three-component force test, the bottom plate 111 with the reinforcing rib 1111 is fixed on the ground, thereby ensuring the safety and stability of the single-plane three-component force test.

[0085] In one embodiment, by Figure 4 It is shown that, in the embodiment, the rotating assembly 120 comprises:

[0086] The bearing seat 121 is provided with a first recess 1211 at the center of the upper end surface, and the lower end of the bearing seat 121 is connected with the bottom plate 111; in the 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 joint bearing 123 is fixedly arranged at the two bottom groove angles of the first recess 1211 and the two top groove angles formed by the first recess 1211 and the bearing end cover 122;

[0089] The main shaft 124 is arranged at one end in the first recess 1211 and clamped between the four thrust joint bearings 123; the other end of the main shaft 124 is exposed out of the end cover center hole 1221, and the center position of the end surface of the other end of the main shaft 124 is provided with a second recess 1241;

[0090] The first flange plate 125 is arranged at one end in the second recess 1241, and the other end of the first flange plate 125 is connected with the movable connecting piece 130. In the embodiment, the first flange plate 125 and the movable connecting piece 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] Further, the setting of the thrust joint bearing 123 provides the degree of freedom for the rotating assembly 120, and the rotation center of the main shaft 124 is located at the ball center of the thrust joint bearing 123. Therefore, the thrust test can be performed by using the design of the rotating assembly 120, the force arm difference is calculated, and the coefficient of the thrust test value and the actual value is obtained, so as to ensure the accuracy of the thrust test.

[0092] Further, each thrust joint bearing 123 comprises:

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

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

[0095] In an embodiment, as shown in Figure 5 In the embodiment, the movable connecting piece 130 comprises:

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

[0097] A plurality of connecting columns 132, one end of each connecting column 132 is respectively inserted into the first connecting hole; the outer side of all connecting columns 132 is provided with a fastening ring 134, and each connecting column 132 is fixedly connected with the fastening ring 134;

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

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

[0100] Further, the movable connecting piece 130 is directly connected with the solid rocket engine, and when the engine is ignited, the thrust test is performed by using the degree of freedom provided by the rotating assembly 120.

[0101] In an embodiment, as shown in Figure 6 In the embodiment, the force measuring assembly 140 comprises, in sequence: a loose sleeve flange 141, a first adjusting piece 142, a push-pull sensor 143, a second adjusting piece 144, a flexible piece 145, a third adjusting piece 146, and a second flange plate 147;

[0102] One end of the loose flange 141 is fixedly connected with the upper end of the single support column 112, and the other end of the loose flange 141 is connected with the first adjusting piece 142.

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

[0104] Further, the force measuring assembly 140 adopts the structure of the push-pull sensor 143 matched with a flexible piece 145, which can effectively test the lateral force and eliminate the influence of the remaining thrust on the push-pull sensor 143. Meanwhile, the three adjusting pieces make the length of the whole force measuring assembly 140 adjustable, facilitating installation. In the embodiment, the three adjusting pieces can all adopt the mode of the adjusting nut matched with the adjusting screw rod to adjust the length of the force measuring assembly 140.

[0105] Further, in the embodiment, three force measuring assemblies 140 are installed on the force measuring plane, i.e., one is installed on the upper end of the single support column 112, and the other two are installed on the upper end of an adjacent double support column 113, so that the overall roll caused by the thrust of the solid rocket engine can be eliminated while the force is measured, ensuring the reliability of the single-plane three-component test.

[0106] In one embodiment, the force measuring assembly 140 includes a push-pull sensor 143 and a flexible piece 145. Figure 7 and Figure 8 As shown in the drawings, in the embodiment, the limiting assembly 150 includes:

[0107] A limiting rod 151, the bottom end of the limiting rod 151 is arranged on the bottom plate 111, and the upper end of the limiting rod 151 is connected with the upper flange plate 131.

[0108] A plurality of locking assemblies 152, the limiting rod 151 is sequentially sleeved with the plurality of locking assemblies 152 from top to bottom, and each locking assembly 152 includes a sleeve ring 1521, a locking nut 1522 and a backup nut 1523 connected in sequence. In the embodiment, two locking assemblies 152 are arranged on the limiting rod 151. After the sleeve ring 1521 is sleeved on the limiting rod 151, the locking nut 1522 is twisted, and the whole single-plane three-component test device 100 is kept in a fixed state by the upper and lower locking assemblies 152.

[0109] Further, the limiting assembly 150 is connected with the bottom plate 111 through the limiting rod 151 and is pressed tightly from top to bottom by using the locking nut 1522 and the lower flange plate 133 of the movable connecting piece 130. When the single-plane three-component test is in a preparation state, the locking nut 1522 is twisted and locked from top to bottom; when the solid rocket engine is installed and the preliminary preparation work is completed, the locking nut 1522 is loosened from top to bottom, and at this time, the solid rocket engine is in a test state.

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

[0111] The entire working process of the single-plane three-component force test using the single-plane three-component force test device can include the following steps, as shown in Figure 9

[0112] Step S101: connect the solid rocket engine with 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 disc in the force measuring assembly at the upper end of the double-body support column or the upper end of the single-body support column, and fix the loose flange disc with the movable connecting piece.

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

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

[0117]

[0118] wherein F represents the final force, 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 limiting assembly to make the rotating assembly in a free state, and according to the single-plane three-component force test mechanical model, use the force measuring assembly to measure the data of the solid rocket engine.

[0120] Step S106: after the ignition test, calculate the measurement data according to the moment 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-component 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 the technical features indicated. Therefore, 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 this application, the meaning of "plurality" is two or more, unless otherwise clearly specified.

[0123] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" mean 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 expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification.

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

[0125] Those skilled in the art will readily appreciate other embodiments of the present invention after considering the specification and practicing the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of the present invention that follow the general principles of this application and include common knowledge or customary techniques in the art that are not disclosed herein.

Claims

1. A solid rocket engine single-plane three-force test device, characterized in that: include: A support assembly, the support assembly comprising a base plate, and a pair of opposed single-body support columns and a pair of opposed double-body support columns disposed on the base plate, wherein a center point of a central axis between two of the single-body support columns and a center point of a central axis between two of the double-body support columns coincide with each other and are projected onto a point on the base plate, the projection point being defined as the projection point; a rotating assembly, the lower end of which is connected to the base 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 connect to the engine; A plurality of force-measuring assemblies, wherein 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 member; a limiting assembly, wherein the lower end of the limiting assembly is connected to the base plate, and the upper end of the limiting 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 solid rocket engine single-plane three-force test device according to claim 1, characterized in that: The double support column includes: two single support columns connected to each other, and the two single support columns are connected by a second support beam.

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

4. The solid rocket engine single-plane three-force test device according to claim 2, characterized in that: The rotating assembly comprises: A bearing seat, wherein a first groove is provided 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, the bearing end cover is arranged at the upper end of the bearing seat, and the bearing end cover is provided with an end cover center hole; A thrust spherical bearing, wherein the two bottom groove corners of the first groove and the two top groove corners formed by the first groove and the bearing end cover are respectively fixedly provided with the thrust spherical bearing; A main shaft, one end of which is disposed 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 provided 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 solid rocket engine single-plane three-force test device 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; A movable joint, one end of the movable joint is movably connected to the other end of the fixed joint, and the other end of the movable joint is connected to the main shaft.

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

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

9. A single-plane three-force test method for a solid rocket motor, characterized in that: The three-force test method is performed using the test device according to any one of claims 1 to 8, and the test method comprises the following steps: connecting the solid rocket motor to the movable connector 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 support column or the upper end of the single support column, and fixedly connecting the loose flange to 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 released to place the rotating assembly in a free state, and data measurement of the solid rocket motor is performed using the force measurement assembly according to the single-plane three-force test mechanical model. After the ignition test, the measurement data is resolved according to the torque ratio of the test device.

10. The single-plane three-force test method for a solid rocket motor 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 Indicates the actual thrust in the x-axis direction, F y Indicates 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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