A rocket engine radiation field measurement device

Abstract

The present invention provides a rocket engine radiation field measurement device, comprising: a heat flux sensor, arranged outside an explosion-proof test chamber; a plurality of optical fibers, the first ends of the plurality of optical fibers are spaced and distributed in the explosion-proof test chamber; the second ends of the plurality of optical fibers form an arc region; the heat flux sensor is suitable for measuring the thermal radiation transmitted by the optical fibers; a rotating shaft, arranged at the center of the arc region; the rotating shaft is connected to the heat flux sensor; the heat flux sensor rotates in the arc region to match the arc region; during the rotation of the heat flux sensor, the detection end of the heat flux sensor is aligned with the second end of each optical fiber in sequence; and a collector is connected to the heat flux sensor for communication. It saves the cost of purchasing many heat flux sensors in the prior art, reduces the high temperature resistance and explosion-proof requirements for heat flux sensor materials and corresponding equipment, and the collector can select a model with fewer sampling channels to reduce related costs.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engine testing, and in particular to a rocket engine radiation field measuring device. Background Art

[0002] The thermal radiation field of the rocket engine gas tail flame is relatively large. To analyze the heat flow of the radiation field, the existing technology requires many heat flow sensors to distribute the measurement points. However, heat flow sensors are expensive, and too many measurement points will also place higher requirements on the acquisition system, requiring more sampling channels. In addition, the temperature of the rocket engine tail flame is high and the explosion-proof level of the environment is high, which puts high requirements on the heat resistance and explosion-proof level of the heat flow sensor, greatly increasing the measurement cost. Summary of the invention

[0003] Therefore, the technical problem to be solved by the present invention is to overcome the defects of the prior art that a large number of thermal flow sensors need to be purchased and the explosion-proof problem of sensors and acquisition equipment needs to be considered, resulting in high testing costs.

[0004] In order to solve the above technical problems, the present application provides a rocket engine radiation field measurement device, which is used for measuring the thermal radiation field of the rocket engine gas tail flame in the explosion-proof test workshop, and includes:

[0005] The heat flow sensor is installed outside the explosion-proof test room;

[0006] A plurality of optical fibers, wherein the first ends of the plurality of optical fibers are spaced apart and distributed in the explosion-proof test chamber; the second ends of the plurality of optical fibers form an arc-shaped area; and the heat flow sensor is suitable for measuring the heat radiation transmitted by the optical fibers;

[0007] A rotating shaft is arranged at the center of the arc region; the rotating shaft is connected to the heat flux sensor; the heat flux sensor rotates in the arc region to match the arc region; during the rotation of the heat flux sensor, the detection end of the heat flux sensor is aligned with the second end of each optical fiber in sequence;

[0008] The collector is communicatively connected with the heat flow sensor.

[0009] Optionally, it further comprises: an arc frame, which is arranged in the arc region, and the center of the arc frame coincides with the center of the arc region; the second ends of the plurality of optical fibers are clamped on the arc frame and are distributed at intervals along the arc of the arc frame.

[0010] Optionally, the first ends of the optical fibers are arranged in sequence, and the second ends of the optical fibers are distributed at intervals along the arc of the arc frame in the order of the sequence arrangement.

[0011] Optionally, the first ends of the optical fibers are distributed at equal intervals.

[0012] Optionally, the second ends of the optical fibers are distributed at equal angles.

[0013] Optionally, the rotating shaft is driven by an intermittent rotating mechanism; the rotation angle of each working step of the intermittent rotating mechanism is equal to the angle difference between the second ends of each optical fiber; and the stopping action is performed when the detection end of the heat flow sensor is aligned with the second end of the optical fiber.

[0014] Optionally, the rotating shaft is driven by a servo motor.

[0015] Optionally, the optical fiber in the explosion-proof test room is coated with a heat insulation layer.

[0016] Optionally, the arc frame is ring-shaped.

[0017] By adopting the above technical solution, the present invention has the following technical effects:

[0018] 1. The rocket engine radiation field measurement equipment provided by the present invention uses optical fiber as an intermediary to indirectly measure thermal radiation, so that soft optical fibers can be gathered from various places in the explosion-proof test room. When the radiation field of the engine tail flame is stable, the heat flux is basically stable. It can be considered that the heat flux is constant during the period of stable engine ignition, and the heat flux sensor responds quickly. Therefore, a heat flux sensor can be used to rotate intermittently at a uniform speed in a small space to measure each optical fiber measurement point after convergence in turn, and indirectly measure the thermal radiation of the rocket engine tail flame in the explosion-proof test room, thereby saving the cost of purchasing many heat flux sensors in the prior art, and the collector can use a single or less sampling channel model, effectively reducing the relevant costs.

[0019] 2. The rocket engine radiation field measurement device provided by the present invention can realize simple linear and spatial thermal radiation measurement through multiple methods such as linear arrangement and spatial distribution of optical fibers. If a large-area thermal radiation field measurement is required, the amount of heat flux sensors can be greatly reduced to a certain extent by increasing the number of optical fibers or adding multiple sets of devices of this embodiment. In addition, if the ignition time of the rocket engine is short, that is, the measurement time is short, multiple sets of devices of this embodiment can be set. Although the number of optical fibers responsible for each heat flux sensor is reduced, each set of optical fibers can be polled more quickly to increase the sampling rate.

[0020] 3. The rocket engine radiation field measurement equipment provided by the present invention has a first end of each optical fiber that can be distributed around the rocket engine according to measurement needs. The optical fiber is easy to fix and hang. This method can more objectively reflect the distribution state of the thermal radiation of the rocket engine, which is conducive to understanding the thermal radiation field from a local or overall perspective.

[0021] 4. The rocket engine radiation field measurement equipment provided by the present invention has the second end of the optical fiber evenly distributed in a circular shape, and the detection end of the heat flux sensor can be aligned with the optical fiber every time it rotates through a specific angle, so that a mechanized rotation and sampling system can be easily set up.

[0022] 5. The rocket engine radiation field measurement equipment provided by the present invention adopts an intermittent rotation mechanism to drive the rotating shaft. Each rotation aligns the detection end of the heat flux sensor with the second end of the next optical fiber, and takes a short break to complete accurate measurement, thereby ensuring a higher measurement accuracy.

[0023] 6. The rocket engine radiation field measurement equipment provided by the present invention adopts a servo motor to drive the rotating shaft. Because the number of optical fibers arranged on the same arc frame is usually large, the use of a mechanical intermittent mechanism will result in a complex structure and heavy weight. The use of a servo motor simplifies the installation process and reduces the weight of the entire device.

[0024] 7. The rocket engine radiation field measurement equipment provided by the present invention does not require insulation or explosion-proof treatment for the optical fiber part in the explosion-proof test chamber, except for the part outside the test chamber that needs to be wrapped with a heat insulation layer. This makes it unnecessary to put forward high-level high-temperature resistance and explosion-proof requirements for electrical components such as heat flux sensors and collectors, so that ordinary models can be purchased for use, which greatly reduces the procurement demand for special equipment, not only reduces related costs, but also increases the range of optional replaceable products, which is beneficial to the daily maintenance of this set of equipment.

[0025] 8. The rocket engine radiation field measurement equipment provided by the present invention has an optical fiber partially covered with a heat-insulating layer in the explosion-proof test room. Because some types of rocket engines have large thermal radiation, the optical fiber surface absorbs too much heat radiation and is easily burned, affecting the measurement. Therefore, it is preferred to cover the outer layer of the optical fiber with a heat-insulating layer to reduce the optical fiber's own heat absorption during the test and improve the test accuracy.

[0026] 9. The rocket engine radiation field measurement equipment provided by the present invention has an arc frame that forms a complete circular ring shape, which can accommodate more optical fibers and facilitates the arrangement of the optical fibers at equal intervals, thereby facilitating the matching of the intermittent rotation frequency of the servo motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0028] Figure 1 It is a schematic structural diagram of an embodiment of the present invention.

[0029] Description of reference numerals:

[0030] 1 - rocket engine, 2 - optical fiber, 3 - arc frame, 4 - rotating shaft, 5 - servo motor, 6 - data collector, 7 - connecting rod, 8 - heat flux sensor, 9 - thermal insulation layer, 10 - explosion-proof test workshop, 11 - general measurement and control room. DETAILED DESCRIPTION

[0031] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0032] It should be noted that in the description of the present invention, the directions or positional relationships indicated by terms such as "center", "up", "down", "left", "right", "vertical", "horizontal", "inside" and "outside" are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention.

[0033] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0035] This embodiment provides a rocket engine radiation field measurement device.

[0036] In one embodiment, if Figure 1As shown, it includes: a rotating shaft 4, a heat flux sensor 8, a collector 6 and a plurality of optical fibers 2. The first ends of the optical fibers 2 are spaced apart from each other in the rocket engine radiation field, that is, in the explosion-proof test room 10; their distribution depends on factors such as the span or area of ​​the test site, the distance between the measuring point and the engine position, and the arrangement of the measuring points. The position of the optical fiber end can also be adjusted to achieve the measurement of single-point multi-angle radiation and the measurement of scattered points of the measured object. The second ends of the optical fibers 2 form an arc area. It should be noted that the arc area does not specifically refer to a shape that must be an incomplete arc, and it can completely form a complete circular ring to accommodate more optical fibers 2. The rotating shaft 4 is coaxial with the arc of the arc area. The heat flux sensor 8 is arranged in a common measurement and control room 11 isolated from the explosion-proof test room 10, so that it is not directly affected by the thermal radiation generated by the rocket engine radiation field. The heat flux sensor 8 is connected to the rotating shaft 4 through a connecting rod 7 to rotate in a manner matching the arc area. During the rotation of the heat flow sensor 8, the detection end of the heat flow sensor 8 is aligned with the second end of each optical fiber 2 in sequence to detect the thermal radiation transmitted by the optical fiber 2. The heat flow sensor 8 is preferably non-contact. The collector 6 is connected to the heat flow sensor 8 for collecting the sampling signal of the heat flow sensor 8.

[0037] Because of the indirect measurement method of tail flame heat radiation to optical fiber 2 and then to heat flux sensor 8, as well as the attenuation of optical fiber transmission, the device needs to perform coefficient correction before formal measurement, that is, reading verification. After the correct heat flux is generated at the first end of optical fiber 2, the reading is read on the side of heat flux sensor 8 to obtain the correction coefficient to eliminate systematic deviations.

[0038] Because the device uses optical fiber 2 as an intermediary to indirectly measure thermal radiation, the soft optical fiber 2 can be gathered from various places in the explosion-proof test room 10. When the radiation field of the engine tail flame is stable, the heat flux is basically stable, and the heat flux sensor responds quickly. Therefore, a heat flux sensor 8 can be used to rotate at a uniform speed and intermittently in a small space to measure the converged optical fiber measurement points in turn, thereby saving the cost of purchasing many heat flux sensors 8 in the prior art, and the collector 6 can use a single or fewer sampling channel model, effectively reducing the relevant costs. And after such a setting, the electrical components such as the heat flux sensor 8 and the matching collector 6 no longer need to put forward high-level high temperature resistance and explosion-proof requirements, so that ordinary model products can be purchased for use, which greatly reduces the purchase demand for special equipment, not only reduces the relevant costs, but also increases the range of selectable products that can be replaced, which is beneficial to the daily maintenance of this set of equipment.

[0039] Based on the above embodiment, in a preferred embodiment, Figure 1As shown, it also includes: an arc frame 3, which is arranged in the arc region, and the center of the arc frame 3 coincides with the center of the arc region; the second ends of the plurality of optical fibers 2 are clamped on the arc frame 3 and are distributed at intervals along the arc of the arc frame 3. By clamping the second ends of the optical fibers 2 by the arc frame 3, the extension length of the optical fibers 2 can be easily adjusted, so as to adjust the gap between the heat flow sensor 8 and the optical fibers 2, and make the gaps uniform, thereby providing a more uniform reference for coefficient calibration.

[0040] Based on the above embodiment, in a preferred embodiment, Figure 1 As shown, the first ends of the optical fibers 2 are arranged in sequence, such as linear arrangement, circular arrangement or other orderly arrangement, and the second ends of the optical fibers 2 are distributed along the arc of the arc frame 3 in the order of the aforementioned sequence arrangement. Figure 1 The rocket engine 1 is arranged in a front-to-back order to perform the simplest linear thermal radiation measurement. If an area-type thermal radiation field measurement is required, multiple groups of devices of this embodiment can be arranged in parallel. Compared with the prior art, the amount of heat flux sensor 8 is reduced to a certain extent, and the number of optical fibers responsible for each heat flux sensor 8 is reduced, and each group of optical fibers can be polled more quickly to increase the sampling rate, which is especially suitable for rocket engine ignition time, that is, when the measurement time is short. In addition, this arrangement and connection relationship allows the linear sequence distance of each measuring point on the test field to be converted into an angular sequence deflection on the arc frame 3, so that the heat flux sensor 8 can be quickly rotated to the end of the optical fiber corresponding to the adjacent point on the test field, which is convenient for local area measurement.

[0041] Based on the above embodiment, in a preferred embodiment, Figure 1 As shown, the second ends of the optical fibers 2 are distributed at equal angles, that is, they are evenly distributed along the circumference. The rotation operation of the heat flow sensor 8 can be operated manually under certain circumstances, and after the optical fibers 2 are evenly distributed along the circumference, the heat flow sensor 8 can be aligned with the optical fibers 2 every time it rotates through a specific angle, so that a mechanized rotation and sampling system can be conveniently set up, for example, the rotating shaft 4 can preferably be driven by an intermittent rotation mechanism.

[0042] Since the heat flux sensor responds quickly, the heat flux sensor 8 can be rotated continuously to measure the degree during the rotation process, but it is not as accurate as reading after being completely aligned and left to stand, especially because the device adopts indirect measurement means, various aspects are prone to accumulated errors. Therefore, it is preferred to use an intermittent rotation mechanism to drive the rotation of the shaft 4, and the rotation angle of each step of the intermittent rotation mechanism is equal to the angle difference between the second ends of each optical fiber 2; the heat flux sensor 8 stops when the detection end is aligned with the second end of the optical fiber 2. In this way, each rotation of the intermittent rotation mechanism aligns the heat flux sensor 8 with the second end of the next optical fiber 2, and stops for a while to complete accurate measurement, thereby ensuring a high measurement accuracy.

[0043] The intermittent rotation mechanism can adopt a conventional mechanical intermittent mechanism, such as a cam intermittent mechanism, but the present embodiment preferably adopts a servo motor 5 to drive the rotating shaft 4. Because the number of optical fibers arranged on the same arc frame 3 is usually large, the mechanical intermittent mechanism has a complex structure and heavy weight, while the servo motor 5 simplifies the installation process and reduces the weight of the entire device.

[0044] Based on the above embodiment, in a preferred embodiment, Figure 1 As shown, the optical fiber 2 in the explosion-proof test chamber 10 is coated with a heat insulation layer 9, such as an asbestos layer. Because some models of rocket engines have large thermal radiation, or the optical fiber 2 extends too long into the explosion-proof test chamber 10, the surface of the optical fiber 2 absorbs too much heat radiation and is easily burned, affecting the measurement. Therefore, it is preferred to coat the outer layer of the optical fiber with a heat insulation layer to reduce the optical fiber's own heat absorption during the test process and improve the test accuracy.

[0045] Obviously, the above embodiments are merely examples for clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived from them are still within the protection scope of the invention.

Claims

1. A rocket engine radiation field measurement device, used for measuring the thermal radiation field of the rocket engine gas tail flame in an explosion-proof test room (10), characterized in that: include: A heat flow sensor (8) is arranged in a place isolated from the explosion-proof test room (10); A plurality of optical fibers (2), wherein first ends of the plurality of optical fibers (2) are spaced apart and distributed in the explosion-proof test chamber (10); second ends of the plurality of optical fibers (2) form an arc-shaped area; and the heat flow sensor (8) is suitable for measuring the heat radiation transmitted by the optical fibers (2); An arc frame (3) is arranged in the arc region, and the center of the arc frame (3) coincides with the center of the arc region; the second ends of the plurality of optical fibers (2) are clamped on the arc frame (3) and are distributed at intervals along the arc of the arc frame (3); the first ends of the optical fibers (2) are arranged in sequence, and the second ends of the optical fibers (2) are distributed at intervals along the arc of the arc frame (3) in the order of the sequence arrangement; A rotating shaft (4) is arranged at the center of the arc region; the rotating shaft (4) is connected to the heat flow sensor (8); the heat flow sensor (8) rotates in the arc region to match the arc region; during the rotation of the heat flow sensor (8), the detection end of the heat flow sensor (8) is aligned with the second end of each optical fiber (2) in sequence; A collector (6) is communicatively connected to a heat flow sensor (8); By adopting an indirect measurement method in which the heat radiation from the tail flame is transmitted to the optical fiber (2) and then to the heat flux sensor (8), and the attenuation of the optical fiber transmission, the device needs to perform coefficient correction before formal measurement, that is, reading verification. After a heat flux of a certain value is generated at the first end of the optical fiber (2), the reading is read on the side of the heat flux sensor (8), thereby obtaining a correction coefficient to eliminate systematic deviations.

2. A rocket engine radiation field measurement device according to claim 1, characterized in that: The second ends of the optical fibers (2) are distributed at equal angles.

3. A rocket engine radiation field measurement device according to claim 2, characterized in that: The rotating shaft (4) is driven by an intermittent rotating mechanism; the rotation angle of each working step of the intermittent rotating mechanism is equal to the angle difference between the second ends of each optical fiber (2); and a pause action is performed when the detection end of the heat flow sensor (8) is aligned with the second end of the optical fiber (2).

4. A rocket engine radiation field measurement device according to claim 3, characterized in that: The rotating shaft (4) is driven by a servo motor (5).

5. The rocket engine radiation field measurement device according to claim 1, characterized in that: The optical fiber (2) in the explosion-proof test room (10) is coated with a heat insulation layer (9).

6. The rocket engine radiation field measurement device according to claim 1, characterized in that: The arc-shaped area is ring-shaped.

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