Complete machine level ground static test device for solid attitude and orbit control engine

Abstract

A complete machine level ground static test device for a solid attitude and orbit control engine is characterized in that the complete machine level ground static test device comprises a test bench body, a vector thrust test platform, a high-speed infrared camera mechanism and a non-contact plume impact force test mechanism, the test bench body is fixedly connected with the ground, the vector thrust test platform is fixed above the test bench body, and the non-contact plume impact force test mechanism is fixed above the vector thrust test platform. The test bed body is used for bearing an engine, the high-speed infrared camera shooting mechanism is fixed above the test bed body, the non-contact plume impact force testing mechanism is fixed on the test bed body, and the test bed body comprises a T-shaped table top, a supporting stand column, an A-shaped supporting frame, an equipment placement platform, a cable bundling rod, an upper side sealing plate, an L-shaped supporting plate and a measurement and control cable protection groove. According to the test device, the accuracy and reliability of each test result can be ensured, each test measurement and control device can be reasonably protected, test system errors caused by independent work of each system are reduced, and the test device is an important way for realizing a complete machine level ground static test.

Description

Technical Field

[0001] The present invention belongs to the technical field of engine whole - machine - level ground tests, and particularly relates to a whole - machine - level ground static test device for a solid attitude and orbit control engine. Background Technique

[0002] A solid attitude and orbit control engine is a core component for the attitude and orbit control of space vehicles such as missiles. Its principle is to form a high - pressure gas flow control force in the surrounding channels by modulating control signals. This force constitutes a moment relative to the centroid of the space vehicle, realizing the adjustment of the orbit and attitude of the vehicle during flight, and preventing the missile from deviating from the original required orbit and attitude and thus deviating from the predetermined target. The magnitude of the high - pressure gas flow force ejected by the solid attitude and orbit control engine and its variation law over time characterize the performance of the engine and directly affect the maneuverability of the missile. In the whole - machine - level ground static test of the solid attitude and orbit control engine, the engine thrust, control module, internal ballistic performance, etc. are all assessment targets. Therefore, the whole - machine - level ground static test cannot do without the whole - machine - level ground static test system device for the solid attitude and orbit control engine.

[0003] At present, most of the whole - machine - level test system devices for solid attitude and orbit control engines are for single - item tests. There are few whole - machine - level test devices that take into account both attitude control and orbit control thrust tests, thrust in - situ calibration, and control functions at the same time. This makes the single - item test data obtained from the solid attitude and orbit control engine test different from the test data in the comprehensive operation. Therefore, a whole - machine - level ground static test is required to obtain more accurate test data. Summary of the Invention

[0004] To solve the above - mentioned technical problems, the present invention discloses a whole - machine - level ground static test device for a solid attitude and orbit control engine, which is characterized in that it includes a test bench body, a vector thrust test platform, a high - speed infrared camera mechanism, and a non - contact plume impact force test mechanism. The test bench body is fixedly connected to the ground. The vector thrust test platform is fixed above the test bench body and is used to carry the engine. The high - speed infrared camera mechanism is fixed above the test bench body, and the non - contact plume impact force test mechanism is fixed on the test bench body.

[0005] The test bench body includes a T - shaped tabletop, support columns, an A - shaped support frame, an equipment placement platform, a cable bundling rod, an upper side sealing plate, an L - shaped support plate, and a measurement and control cable protection groove. A product sensor is connected above the T - shaped tabletop. The support columns are arranged under the T - shaped tabletop. There is an A - shaped support frame between the two support columns. An equipment placement platform is arranged at the 1 / 3 position of the support column. A cable bundling rod is arranged on the equipment placement platform. There is an upper side sealing plate between the equipment placement platform and the T - shaped tabletop. There is an L - shaped support plate under the equipment placement platform. The measurement and control cable protection groove is tightly connected to the L - shaped support plate.

[0006] Further, the T-shaped tabletop is provided with criss-cross T-shaped grooves on the entire tabletop, and a rectangular plane and a rectangular opening are provided at its center.

[0007] Further, the T-shaped tabletop and the equipment placement platform are provided with slots, and the equipment placement platform is provided with threaded holes and wire routing openings.

[0008] Further, the L-shaped support plate is provided with a rectangular opening and a threaded hole.

[0009] Further, the high-speed infrared camera mechanism includes a bottom plate, a support rod, a diagonal brace, a support crossbeam, a crossbeam diagonal brace, and a high-speed infrared camera protective cover.

[0010] Further, the bottom plate is connected to the T-shaped tabletop, the support rod is fixedly connected to the bottom plate, the diagonal brace is tightly connected to the support rod, the support crossbeam is tightly connected between the two support rods, and a crossbeam diagonal brace is provided and tightly connected thereto. The high-speed infrared camera protective cover is arranged in the middle of the support crossbeam.

[0011] Further, the support rod is provided with a cable protection groove, and the support crossbeam is provided with a cable protection groove, a track slot hole, and an oblong hole.

[0012] Further, the non-contact plume impact force testing mechanism includes an L-shaped plate, a moving flat plate, and a diversion force measuring plate.

[0013] Further, the L-shaped plate is fixed above the T-shaped tabletop, the moving flat plate is tightly connected to the L-shaped plate, and the diversion force measuring plate is arranged in the middle of the moving flat plate.

[0014] Further, the angle between the diversion force measuring plate on the non-contact plume impact force testing mechanism and the horizontal plane is 60°.

[0015] The present invention has the following advantages:

[0016] (1) It can effectively protect all on-site participating equipment and cables in the ground static test of the solid attitude and orbit control engine, preventing problems such as ablation damage to on-site participating equipment and cables caused by high-temperature gas flow during engine test runs or loosening of cable joints caused by oscillation, resulting in unreliable test data.

[0017] (2) After the multi-component force sensors and the non-contact plume impact force testing mechanism are installed in place with the same reference, the test error caused by inconsistent installation references is effectively reduced.

[0018] (3) By installing the high-speed infrared video shooting device from the top-down shooting perspective directly above the test bench body, the working conditions of each valve can be obtained through a single set of equipment, improving the use efficiency of the test equipment.

[0019] (4) The integrated test system device provided by the present invention can not only ensure the accuracy and reliability of each test result, but also reasonably protect each tested measurement and control device and reduce the test system error caused by the independent operation of each system. Description of the Drawings

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings. It should be noted that for clarity and ease of illustration, the drawings are not necessarily drawn to scale.

[0021] Figure 1 It is a schematic diagram of the overall structure of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0022] Figure 2 It is a schematic diagram of the test bench structure of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0023] Figure 3 It is a schematic diagram of the high-speed infrared mechanism structure of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0024] Figure 4 It is a schematic diagram of the non-contact plume impact force test mechanism of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0025] Figure 5 It is a top view and side view of the T-shaped tabletop of the test bench of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0026] Figure 6 It is a top view of the equipment placement platform of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0027] Figure 7 It is a front view of the L-shaped support plate of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0028] Figure 8 It is a partial front view and top view of the support rod of the high-speed infrared camera mechanism of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0029] Figure 9 It is a front view, top view and left view of the cross beam of the high-speed infrared camera mechanism of the ground static test device at the whole-machine level of the solid attitude and orbit control engine of the present invention;

[0030] Figure 10Schematic structural diagram of the high-speed infrared camera protective cover of the solid attitude and orbit control engine full-machine ground static test device of the present invention;

[0031] Figure 11 Schematic diagram of the plume impact force test plate of the solid attitude and orbit control engine full-machine ground static test device of the present invention.

[0032] Explanation of reference numerals:

[0033] 1 - Test bench body, 2 - Vector thrust test system, 3 - High-speed infrared test mechanism, 4 - Non-contact plume impact force test mechanism, 1-1 - T-shaped tabletop, 1-2 - Support column, 1-3 - A-shaped support frame, 1-4 - Equipment placement platform, 1-5 - Cable bundling rod, 1-6 - Upper side sealing plate, 1-7 - L-shaped support plate, 1-8 - Cable protection groove, 1-11 - T-shaped groove, 1-12 - Rectangular plane, 1-13 - Cable routing opening on the rectangular plane, 1-14 - Slot, 1-15 - Threaded hole, 1-16 - Opening for fastening the equipment and the cable bundling rod and cable routing, 1-17 - Cable routing opening on the L-shaped support plate, 1-18 - Threaded hole of the cable protection groove, 3-1 - Bottom plate, 3-2 - Support rod, 3-3 - Diagonal brace, 3-4 - Cross beam, 3-5 - Cross beam diagonal brace, 3-6 - Outer protective cover of the high-speed infrared camera, 3-11 - Cable protection groove of the support rod, 3-12 - Cable protection groove of the cross beam, 3-13 - Track slot hole of the high-speed infrared camera protective cover, 3-14 - Waist-shaped long through hole, 3-15 - High-speed infrared camera protective cover, 4-1 - L-shaped plate, 4-2 - Equipment flat plate, 4-3 - Flow guiding force measuring plate, 4-11 - Angle between the inclined plane of the flow guiding force measuring plate and the horizontal plane. Specific embodiments

[0034] The present invention will be further described below with reference to the accompanying drawings.

[0035] In this embodiment, as shown in Figure 1 the overall structural schematic diagram of the solid attitude and orbit control engine full-machine ground static test device, it includes a test bench body 1 fixedly connected to the test ground, a vector thrust test platform 2 fixed above the test bench body, a high-speed infrared imaging mechanism 3 fixed above the test bench body, and a non-contact plume impact force test mechanism 4 fixed on the test bench body 1.

[0036] As shown in Figure 2As shown in the schematic diagram of the test bench structure of the solid attitude and orbit control engine at the whole-machine level for ground static tests, in the test bench 1, a total of 9 columns are fixed at the four corners of the test T-shaped tabletop 1-1 and at the positions between every two columns on the support columns 1-2; the A-shaped support frame 1-3 is fixed on the support columns 1-2; the equipment placement platform 1-4 is fixed at about 1 / 3 of the distance from the bottom surface of the support columns; the cable bundling rod 1-5 is fixed on the equipment placement platform 1-4 as required; the upper side sealing plate 1-6 is installed by inserting it into the slot between the T-shaped tabletop test 1-1 and the equipment placement platform 1-4; the L-shaped support plate 1-7 is fixed on the equipment placement platform 1-4; the cable protection groove 1-8 is fixed on the L-shaped support plate 1-7.

[0037] As Figure 3 As shown in the schematic diagram of the high-speed infrared mechanism of the solid attitude and orbit control engine at the whole-machine level for ground static tests, in the high-speed infrared camera mechanism, the bottom plate 3-1 is fixed to the test T-shaped tabletop 1-1; the support rod 3-2 is fixed at the center position of the bottom plate 3-1; one end of the diagonal brace 3-3 is fixed on the bottom plate 3-1, and the other end is fixed on the support rod 3-2; the cross beam 3-4 is fixed at the top position of the support rod 3-2; one end of the cross beam diagonal brace 3-5 is fixed on the cross beam 3-4, and one end is fixed on the support rod 3-2; the outer protective cover 3-6 of the high-speed infrared camera is fixed at the position of the track groove in the middle of the cross beam 3-4 by screws.

[0038] As Figure 4 As shown in the schematic diagram of the non-contact plume impact force test mechanism of the solid attitude and orbit control engine at the whole-machine level for ground static tests, in the non-contact thrust test mechanism for attitude control at the hundred-newton level, the short side of the L-shaped plate 4-1 is fixed to the T-shaped tabletop 1-1; the flat plate 4-2 for installing sensor equipment is fixed to the long side of the L-shaped plate 4-1; a flow guiding force measuring plate 4-3 with a small thrust sensor is installed on the equipment flat plate 4-2.

[0039] As Figure 5 As shown in the top view and side view of the T-shaped tabletop of the test bench of the solid attitude and orbit control engine at the whole-machine level for ground static tests, the T-shaped tabletop is provided with a number of T-shaped grooves 1-11 that crisscross horizontally and vertically for equipment installation; a rectangular plane 1-12 for installing and positioning tabletop equipment is left in the center of the tabletop; openings 1-13 for cable routing are left at the four corners of the positioning rectangular plane.

[0040] As Figure 6 Top view of the equipment placement platform of the solid attitude and orbit control engine at the whole-machine level for ground static tests and Figure 7As shown in the front view of the L-shaped support plate of the static ground test device for the solid attitude and orbit control engine at the whole machine level, a slot 1-14 for installing the upper side seal plate is provided on the equipment mounting plate, and a number of threaded holes 1-15 are arranged at a certain distance on the platform plate of the equipment to be installed for fastening the on-site test equipment and the fastening and wire routing of the cable bundling rod, and an opening 1-16 for wire routing is provided. The L-shaped support plate connected to the ground by expansion screws is provided with an L-shaped support plate wire routing opening 1-17 and cable protection groove threaded holes 1-18 arranged according to the size of the cable protection groove.

[0041] As Figure 8 As shown in the partial front view, top view and Figure 9 As shown in the front view, top view and left view of the cross beam of the high-speed infrared camera mechanism of the static ground test device for the solid attitude and orbit control engine at the whole machine level, the cable protection grooves 3-11 and 3-12 of the support rod are through grooves opened on the support rod and the cross beam respectively, a track groove hole 3-13 for supporting the high-speed infrared camera protective cover is opened in the middle part of the cross beam, and waist-shaped long through holes 3-14 for fastening the outer protective cover 3-6 of the high-speed infrared camera are arranged on both sides of the wire groove.

[0042] As Figure 10 As shown in the structural schematic diagram of the high-speed infrared camera protective cover of the static ground test device for the solid attitude and orbit control engine at the whole machine level, the function of the high-speed infrared camera protective cover 3-15 is to protect the installed high-speed infrared camera.

[0043] As Figure 11 As shown in the schematic diagram of the plume impact force test plate of the static ground test device for the solid attitude and orbit control engine at the whole machine level, the diameter of the columnar flow guiding force measuring plate for thrust test on the hundred-newton non-contact attitude control thrust test mechanism is 3.6 times the diameter of the measured nozzle, and the angle between the inclined surface 4-11 of the flow guiding force measuring plate and the horizontal plane is 60°.

[0044] Under the test conditions, the gas valve drive control device is fastened and locked to the equipment mounting plate by screws through the through holes of the controller itself; the control power supply device is pressed and connected to the equipment mounting plate by the power fixing pressing plate; the upper side seal plate is inserted into the guiding slot provided by the T-shaped tabletop of the test bench and the equipment mounting plate and then fastened and connected by screws for surrounding closure; the cable protection groove is connected to the L-shaped support plate by screws; the upper side seal plate is fastened and connected to the L-shaped support plate by screws.

[0045] The test device of the present invention can not only ensure the accuracy and reliability of each test result, but also reasonably protect each participating measurement and control equipment and reduce the test system error brought by the independent operation of each system, which is an important way to realize the static ground test at the whole machine level.

[0046] Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and decorations made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention. The content not detailedly described in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims

1. A whole-machine ground static test device for a solid attitude and orbit control engine, characterized in that: It includes a test bench body, a vector thrust test platform, a high-speed infrared camera mechanism, and a non-contact plume impact force test mechanism. The test bench body is fixedly connected to the ground, the vector thrust test platform is fixed above the test bench body to carry the engine, the high-speed infrared camera mechanism is fixed above the test bench body, and the non-contact plume impact force test mechanism is fixed on the test bench body. The test bench body includes a T-shaped table top, supporting columns, an A-shaped supporting frame, an equipment placement platform, a cable bundling rod, an upper side sealing plate, an L-shaped supporting plate, and a measurement and control cable protection groove. The product sensor is connected to the top of the T-shaped table top, the supporting columns are arranged under the T-shaped table top, an A-shaped supporting frame is arranged between two of the supporting columns, an equipment placement platform is fixed to the supporting columns, a cable bundling rod is arranged on the equipment placement platform, an upper side sealing plate is arranged between the equipment placement platform and the T-shaped table top, an L-shaped supporting plate is arranged under the equipment placement platform, and the measurement and control cable protection groove is fastened to the L-shaped supporting plate.

2. A whole-machine ground static test device for a solid attitude and orbit control engine as claimed in claim 1, characterized in that: The entire T-shaped table top is provided with T-shaped grooves that are staggered in both horizontal and vertical directions, and a rectangular plane and a rectangular opening are provided at the center thereof.

3. A whole-machine ground static test device for a solid attitude and orbit control engine as claimed in claim 1, characterized in that: The T-shaped table and the equipment placement platform are provided with slots, and the equipment placement platform is provided with threaded holes and wiring openings.

4. A whole-machine ground static test device for a solid attitude and orbit control engine as claimed in claim 1, characterized in that: The L-shaped support plate is provided with a rectangular opening and a threaded hole.

5. The whole-machine ground static test device for solid attitude and orbit control engine according to claim 1, characterized in that: The high-speed infrared camera mechanism comprises a bottom plate, a support rod, a diagonal brace, a supporting crossbeam, a crossbeam diagonal brace, and a high-speed infrared camera protective cover.

6. The whole-machine ground static test device for solid attitude and orbit control engine according to claim 5, characterized in that: The bottom plate is connected to the T-shaped table top, the support rod is fixedly connected to the bottom plate, the diagonal brace is tightly connected to the support rod, the supporting crossbeam is tightly connected between the two support rods, and a crossbeam diagonal brace is tightly connected to it, and a high-speed infrared camera protective cover is arranged in the middle of the supporting crossbeam.

7. A whole-machine ground static test device for a solid attitude and orbit control engine according to claim 6, characterized in that: The support rod is provided with a cable protection groove, and the support crossbeam is provided with a cable protection groove, a track slot hole and a waist-shaped hole.

8. The whole-machine ground static test device for solid attitude and orbit control engine according to claim 1, characterized in that: The non-contact plume impact force testing mechanism comprises an L-shaped plate, a movable plate, and a flow guide force plate.

9. The whole-machine ground static test device for solid attitude and orbit control engine according to claim 8, characterized in that: The L-shaped plate is fixed above the T-shaped table top, the movable plate is fastened to the L-shaped plate, and the flow guide force measuring plate is arranged in the middle of the movable plate.

10. The whole-machine ground static test device for solid attitude and orbit control engine according to claim 8, characterized in that: The angle between the guide force plate on the non-contact plume impact force testing mechanism and the horizontal plane is 60°.

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