CN112432792A - Solid rocket engine test frame based on magnetic suspension non-contact weak constraint - Google Patents
Solid rocket engine test frame based on magnetic suspension non-contact weak constraint Download PDFInfo
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- CN112432792A CN112432792A CN202011336452.9A CN202011336452A CN112432792A CN 112432792 A CN112432792 A CN 112432792A CN 202011336452 A CN202011336452 A CN 202011336452A CN 112432792 A CN112432792 A CN 112432792A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Abstract
The invention provides a magnetic suspension non-contact weak constraint-based solid rocket engine test frame, which comprises two groups of electromagnetic base static frames, five external electromagnets uniformly distributed in the electromagnetic base static frames, a permanent magnet restraining ring moving frame positioned in the electromagnetic base static frames, five permanent magnets arranged outside the permanent magnet restraining ring moving frame and matched with the external electromagnets, a safety limiting portal frame, a safety limiting snap ring arranged in the safety limiting portal frame, an annular bushing arranged in the safety limiting snap ring, an optical instrument measuring support frame and an optical measuring device arranged on the optical instrument measuring support frame, wherein a thrust frame is arranged on the end face of one group of electromagnetic base static frames, an engine is fixed by the two permanent magnet restraining ring moving frames, and the optical measuring device is used for measuring vibration displacement. The invention has the advantages of simple principle, high adaptability, no contact and weak constraint on the projectile body, and has better application prospect for unstable combustion experiments.
Description
Technical Field
The invention relates to a magnetic suspension non-contact weak constraint-based solid rocket engine test frame, and belongs to the technical field of rocket engine testing.
Background
The unstable combustion of the solid rocket engine means that the pressure of a combustion chamber deviates from the rule predetermined by a designer to form transient pressure change. In the process of multiple test runs, an engine which is successfully tested on the ground has unstable combustion in a flight test, and the conditions of irregular shaking of a shell, deviation of a ballistic curve and even explosion occur. For the inconsistency between the ground test and the flight test, the improvement of the ground test condition is urgently needed, so that the unstable combustion problem can be reproduced on the ground.
The spring-mass system composed of the engine and the test frame can generate vibration under the impact of ignition and shutdown of the engine and the unstable combustion action in the whole working process, the engine is usually locked on the thrust frame by the conventional test bed, and although the engine and the test frame are supported by elastic materials such as universal joints, plate springs and the like, the engine and the test frame are integrated to a certain extent, the original resonance frequency of the engine is changed, the coupling relation between the structure of the engine and the internal instability is inhibited, and the spring-mass system has great influence on the test of the unstable combustion.
Compared with the traditional test frame, the magnetic suspension non-contact weak constraint test frame can separate the engine from the thrust frame, overcomes the self gravity of the engine by the magnetic suspension acting force, does not generate contact constraint on the engine, ensures the degree of freedom and the original resonance frequency of the engine, solves the problem of the consistency of the unstable combustion test in the sky and the ground, and better reproduces the high-altitude real flight working condition.
Disclosure of Invention
The invention aims to provide a solid rocket engine test frame based on magnetic suspension non-contact weak constraint aiming at a test method for unstable combustion of an engine, aiming at the problem that the ground test of the engine cannot reproduce the inconsistency of the high-altitude flight test.
The purpose of the invention is realized as follows: the device comprises two groups of electromagnetic base static frames, five external electromagnets uniformly distributed in the electromagnetic base static frames, a permanent magnet restraint ring moving frame positioned in the electromagnetic base static frames, five permanent magnets matched with the external electromagnets and arranged outside the permanent magnet restraint ring moving frame, a safety limit portal frame, a safety limit snap ring arranged in the safety limit portal frame, an annular bushing arranged in the safety limit snap ring, an optical instrument measurement support frame and an optical measurement device arranged on the optical instrument measurement support frame, wherein the end face of one group of electromagnetic base static frames is provided with a thrust frame, an engine is fixed by the two permanent magnet restraint ring moving frames, and the optical measurement device is used for measuring vibration displacement.
The invention also includes such structural features:
1. the number of the safety limit portal frames is also two, and the two groups of the safety limit portal frames are positioned between the two groups of the electromagnetic base static frames.
2. The safety limit clamping ring is circumferentially provided with three protruding buckles which are respectively positioned at the top end and the left side and the right side, and three grooves matched with the protruding buckles are formed in the inner surface of the safety limit portal frame.
3. The arrangement mode of five external electromagnets is as follows: one at the upper end, one at the left side and the right side, and two at the lower end.
Compared with the prior art, the invention has the beneficial effects that: 1) the solid rocket engine test frame based on magnetic suspension non-contact weak constraint provided by the invention realizes the condition of non-contact constraint on the engine while overcoming the gravity of the engine, releases the degree of freedom of the engine and can realize weak constraint free vibration; 2) the solid rocket engine test frame based on magnetic suspension non-contact weak constraint can adapt to different engine sizes through adjusting the annular bushing; 3) compared with other test frames, the solid rocket engine test frame based on magnetic suspension non-contact weak constraint has the advantages of a separated structure, light weight, high reliability and the like, and compared with other multi-component test frames, the magnetic suspension test frame has the advantage of non-contact support.
Drawings
FIG. 1 is a general assembly drawing of a magnetic levitation based non-contact weak constraint solid rocket engine test frame according to the present invention;
FIG. 2 is an assembly diagram of a core magnetic suspension test frame main body of a solid rocket engine test frame based on magnetic suspension non-contact weak constraint;
FIG. 3 is a suspension structure of a permanent magnet restraint ring moving frame, a safety limit snap ring, an annular bushing, a thrust frame and the like of a magnetic suspension non-contact weak restraint-based solid rocket engine test frame;
FIG. 4 is a diagram of the working configurations of the permanent magnet confinement ring moving frame and the electromagnetic base stationary frame of the present invention and the mating bottom force-bearing permanent magnet, side/top control permanent magnet, bottom force-bearing electromagnet and side/top control electromagnet;
FIG. 5 is a block diagram of the safety limit snap ring and the safety limit portal frame of the present invention;
fig. 6 is an optical measuring device and an optical instrument measurement stand according to the present invention.
In the figure: 1-optical instrument measurement support; 2-an optical measuring device; 3-a safety limit portal frame; 4-an electromagnetic base static frame; 5-testing the engine; 6-a thrust frame; 7-a permanent magnet restraint ring moving frame; 8-a safety limit snap ring; 9-bottom force bearing permanent magnet; 10-side/top control electromagnets; 11-bottom force bearing electromagnet; 12-side/top control permanent magnets; 13-annular bushing.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
With reference to fig. 1 to 6, the test engine of the present invention employs a conventional solid rocket engine, and in order to ensure that the casing is not attracted by the magnet material, the carbon fiber composite material is selected as the engine casing, which has the characteristics of high strength and small mass. Engines with different diameters and lengths can be selected in practical tests, and the fitting size of the rubber annular bushing is changed. The movable frame part and the static frame are designed to be separated in a non-contact weak constraint mode, and free vibration of an engine shell can be guaranteed. The invention includes the optical instrument measures the support frame 1; an optical measuring device 2; a safety limit portal frame 3; an electromagnetic base stationary frame 4; testing the engine 5; a thrust frame 6; the permanent magnet restrains the ring moving frame 7; a safety limit snap ring 8; a bottom force bearing permanent magnet 9; a side/top control electromagnet 10; a bottom force bearing electromagnet 11; side/top control permanent magnets 12; an annular bushing 13. The engine 5 is fixed by two head and tail permanent magnet restraint ring moving frames 7, 5 permanent magnets 9 and 12 are embedded in each moving frame, external electromagnets 10 and 11 are matched, two pairs 911 of the lower parts mainly support the gravity of the spray pipe, and the magnets 10 and 12 on the side parts and the upper parts are used for restraining the displacement range of the spray pipe. The engine head permanent magnet restraint ring movable frame 7 mainly plays a role in supporting gravity, and the tail permanent magnet restraint ring movable frame 7 is mainly used for limiting engine instability possibly caused by high thrust besides playing a role in supporting gravity. Utilize safety limit snap ring 8 and safety limit portal frame 3, guarantee to support the engine and do not drop when electromagnetism became invalid, protection engine and electromagnetism experimental apparatus. The radius of the tested engine can be adjusted through the annular bushing 13, the length of the tested engine can be adjusted through the position of the permanent magnet restraint ring moving frame 7, and the device is suitable for various engine radiuses and lengths.
As shown in figure 1, the main part of the invention consists of a test frame body 3-13 and optical measuring devices 1 and 2, wherein the optical measuring device support frame 1 is at a proper distance from the test frame, so that the optical instrument 2 is ensured to be capable of accurately measuring vibration displacement and is far away from the test frame, and inaccurate measurement data caused by the transmission of high-frequency vibration of the test frame to the measuring device is prevented.
Fig. 2 shows a magnetic levitation test carriage, from which it can be seen that the central body, consisting of the motor 5 and the associated snap ring 78 and the permanent magnets 9, 12, is suspended without contact from the test carriage. The magnetic suspension device is suspended in the portal frame through magnetic suspension acting force and is not contacted with the portal frame. Before the test is started, the engine is hoisted by a crane, the annular rubber bushing 13 and the safety limiting snap ring 8 are installed, and then the permanent magnet restraining ring moving frame 7 and the thrust frame 6 are installed. After the installation, the engine is sequentially pushed into the safety limiting portal frame 3 from the head and the tail of the engine, and after the safety limiting snap ring is aligned with the limiting hole of the safety limiting portal frame, the engine is slowly put down to enable the engine to fall on the safety limiting portal frame. And then, respectively pushing the electromagnetic base static frame from the head and the tail, aligning the positions, and then fixing the portal frame and the static frame, so as to start debugging the magnetic suspension device.
Fig. 3 shows the permanent magnet restraint ring moving frame 7 and the safety limit snap ring 8 and the thrust frame 6 which are installed on the engine. Inside the snap ring, arranged the bush of rubber material, the isolated engine of aim at and restraint ring prevent to become an organic whole, influence the resonant frequency of engine itself, make the engine be connected inseparabler with the restraint ring simultaneously.
Fig. 4 is a diagram showing the matching relationship between the permanent magnet confinement ring moving frame 7 and the electromagnetic base static frame 4, and between the permanent magnets 9 and 12 and the electromagnets 10 and 11. After the magnetic suspension effect, the two magnets are mutually exclusive in the same level, and the acting force enables the lower magnet to jack up the engine and give a suspension standard distance. The combination of the lateral and upper magnets mainly plays a role in preventing instability. After the engine works, the mass center offset caused by the shaking of the engine shell is corrected and returned in time due to the magnetic suspension acting force, but the vibration of the engine is not influenced by only adjusting the center, and the good effect of enabling the engine to vibrate freely without contact is achieved.
Fig. 5 shows a schematic diagram of the cooperation between the safety limit portal frame 3 and the safety limit snap ring 8, and the structure plays different roles in different experimental periods: in the non-working stage of magnetic suspension, the support frame is used as a support frame of an engine; in the magnetic suspension working stage, the safety limiting function is achieved, the safety displacement amount of the magnetic suspension device to each direction is a safety distance which is smaller than the magnetic suspension floating distance, and the magnetic suspension device is protected from collision caused by sudden power failure or overlarge vibration of an engine.
Fig. 6 shows an optical instrument measurement support and an optical measurement device. The fiber bragg grating device is adopted to measure the strain of the engine, and a row of six measuring instruments are adopted to respectively measure different positions of the engine shell. The optical measurement does not influence the mechanical property of the measuring body.
The electromagnetic base static frame is mainly composed of a frame type portal frame, 5 electromagnets are embedded in the inner frame, and the electromagnetic base static frame is composed of 2 bottom bearing electromagnets and 3 side/top control electromagnets respectively. The electromagnet and the base are fixedly connected through bolts.
The permanent magnet restraint ring moving frame is characterized in that an annular bushing is matched and used to be annularly fixed at the head and tail positions of an engine, 5 permanent magnets are embedded, and are respectively a bottom bearing permanent magnet and a side/top control permanent magnet, and the permanent magnets and a base are connected and fixed through bolts.
The electromagnetic base static frame and the permanent magnet restraint ring movable frame are matched for use, and two sets of the electromagnetic base static frame and the permanent magnet restraint ring movable frame are used in the design. The two electromagnets below the static frame interact with the permanent magnet in the movable frame, and mainly bear the gravity support of the engine, the permanent magnet restraint ring movable frame and the safety limit snap ring, so that the engine is suspended in the test area. The side/top electromagnet of the static frame interacts with the permanent magnet at the corresponding position in the moving frame, and is mainly used for bearing the displacement limitation in the working process of the engine. In order to not influence the sound vibration frequency of the engine, the device is respectively arranged at the head and the tail of the shell of the engine, the free vibration of the engine is not influenced while the gravity of the engine is supported by using a magnetic suspension technology, and the sound mode of the engine is not influenced by the installation position.
The annular bushing is made of rubber materials, is arranged between the permanent magnet restraint ring moving frame and the engine and has various sizes. The damping device is mainly used for matching different diameters of engines, simultaneously buffering collision contact between two rigid bodies and fastening outer ring installation.
The thrust frame is a conventional conical thrust frame and is formed by welding and processing 4 steel pipes and steel plates at two ends. The mounting position is at the engine head.
The safety limit snap ring is matched with the annular bushing and installed on an engine shell, the number of the safety limit snap ring and the number of the annular bushing are two, the center of mass of the engine needs to be calculated at the installation position, the engine is located and installed at the 1/3 position of each deviation total length on two sides, the safety limit snap ring is matched with the safety limit portal frame for use, and the purpose is to prevent the engine from falling off due to sudden power failure or sudden factors. The limiting clamp ring has 3 limiting pins, and each limiting pin is a safe distance away from the limiting portal frame. Meanwhile, the limiting portal frame can also ensure the maximum movement safety distance of each direction, and the maximum movement safety distance is smaller than the magnetic suspension distance, so that the magnetic suspension device is protected from being damaged due to abnormal falling or vibration.
The vibration measuring device is mainly used for measuring the displacement of the shell caused by vibration, adopts a non-contact fiber grating to measure strain in order not to influence free vibration, and adopts a distributed measuring technology.
The project designs a solid rocket engine test frame based on magnetic suspension non-contact weak constraint aiming at the problems of the existing engine test frame, and the improvement process of the test frame is as follows:
1) the invention ensures the freedom degree of the engine by changing the fixed installation mode between the engine and the test frame into magnetic suspension constraint;
2) according to the invention, the safety limit snap ring and the safety limit portal frame are arranged, so that the magnetic suspension device is prevented from being damaged due to collision caused by overlarge vibration frequency in the test run process, and the risk that the magnetic suspension failure experiment engine falls off due to sudden power failure is prevented;
3) the strain is measured by using the non-contact fiber bragg grating, and compared with the traditional contact strain measuring device, the natural frequency of the projectile body is not influenced.
To sum up, the invention relates to a solid rocket engine test frame based on a magnetic suspension technology, which is used for testing the combustion instability test of a solid rocket engine on the ground. In the ground test run experiment of the engine, the conventional test frame locks the engine in the frame, and the strong constraint relation restrains shell vibration caused by unstable combustion. The invention separates the engine and the thrust frame by using the magnetic suspension technology, forms a non-contact weak-constraint free vibration condition, simulates the non-constraint flight condition of the engine in the air, and ensures that the condition that the engine fails or even explodes due to abnormal shake caused by the design problem of the engine can be reproduced on the ground. According to the invention, through a magnetic suspension technology, the gravity of the engine can be overcome, the engine can be restrained in a non-contact manner, the space-ground consistency of an engine test is simulated under the ground condition, and the reproduction of the vibration of the projectile body of the engine caused by unstable combustion in high altitude under the ground test condition is ensured. The invention has the advantages of simple principle, high adaptability, no contact and weak constraint on the projectile body, and has better application prospect for unstable combustion experiments.
Claims (5)
1. A solid rocket engine test frame based on magnetic suspension contactless weak constraint is characterized in that: the device comprises two groups of electromagnetic base static frames, five external electromagnets uniformly distributed in the electromagnetic base static frames, a permanent magnet restraint ring moving frame positioned in the electromagnetic base static frames, five permanent magnets matched with the external electromagnets and arranged outside the permanent magnet restraint ring moving frame, a safety limit portal frame, a safety limit snap ring arranged in the safety limit portal frame, an annular bushing arranged in the safety limit snap ring, an optical instrument measurement support frame and an optical measurement device arranged on the optical instrument measurement support frame, wherein the end face of one group of electromagnetic base static frames is provided with a thrust frame, an engine is fixed by the two permanent magnet restraint ring moving frames, and the optical measurement device is used for measuring vibration displacement.
2. The magnetic suspension-based non-contact weak constraint solid rocket engine test frame according to claim 1, characterized in that: the number of the safety limit portal frames is also two, and the two groups of the safety limit portal frames are positioned between the two groups of the electromagnetic base static frames.
3. The magnetic suspension-based non-contact weak constraint solid rocket engine test frame according to claim 1 or 2, characterized in that: the safety limit clamping ring is circumferentially provided with three protruding buckles which are respectively positioned at the top end and the left side and the right side, and three grooves matched with the protruding buckles are formed in the inner surface of the safety limit portal frame.
4. The magnetic suspension-based non-contact weak constraint solid rocket engine test frame according to claim 1 or 2, characterized in that: the arrangement mode of five external electromagnets is as follows: one at the upper end, one at the left side and the right side, and two at the lower end.
5. The magnetic suspension-based non-contact weak constraint solid rocket engine test frame according to claim 3, characterized in that: the arrangement mode of five interior permanent magnets does: one at the upper end, one at the left side and the right side, and two at the lower end.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114152153A (en) * | 2021-11-11 | 2022-03-08 | 重庆零壹空间科技集团有限公司 | Rocket body natural frequency test supporting platform |
| CN114151238A (en) * | 2021-11-26 | 2022-03-08 | 哈尔滨工程大学 | Vertical weak-constraint cold-flow solid rocket engine test bed and pulse triggering experimental device and method |
| CN114233524A (en) * | 2021-10-29 | 2022-03-25 | 中国人民解放军战略支援部队航天工程大学 | Research system for coupling of longitudinal unstable combustion and structural vibration of rocket engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114233524A (en) * | 2021-10-29 | 2022-03-25 | 中国人民解放军战略支援部队航天工程大学 | Research system for coupling of longitudinal unstable combustion and structural vibration of rocket engine |
| CN114233524B (en) * | 2021-10-29 | 2023-03-10 | 中国人民解放军战略支援部队航天工程大学 | Research system for coupling of longitudinal unstable combustion and structural vibration of rocket engine |
| CN114152153A (en) * | 2021-11-11 | 2022-03-08 | 重庆零壹空间科技集团有限公司 | Rocket body natural frequency test supporting platform |
| CN114151238A (en) * | 2021-11-26 | 2022-03-08 | 哈尔滨工程大学 | Vertical weak-constraint cold-flow solid rocket engine test bed and pulse triggering experimental device and method |
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