A coupled heating device for plasma pneumatic heating and radiation heating

Abstract

The present invention relates to the field of aerospace technology, and in particular to a coupled heating device for plasma pneumatic heating and radiant heating; the present invention provides a pneumatic heat source for a sample by using a plasma heater; the radiant heater is located at the focus of a second heat reflecting mechanism, and the radiant heater generates a radiant heat flow that is reflected by the second heat reflecting mechanism to a first heat reflecting mechanism, and the first heat reflecting mechanism then reflects the radiant heat flow and concentrates it on the surface of the sample, thereby realizing convection and radiation coupled heating of the sample, so as to simulate the thermal environment to which a thermal protection layer of a spacecraft is subjected during flight, and further complete the heat insulation assessment of a hypersonic vehicle structure and material, and finally avoid the problem of the failure of internal instruments of the spacecraft to work normally and the safety of personnel due to the internal thermal decomposition of the thermal protection layer of the spacecraft during actual high-speed flight.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a coupled heating device for plasma pneumatic heating and radiation heating. Background Art

[0002] During the high-speed flight of a spacecraft, the thermal protection materials are subjected to severe aerodynamic heating and radiation heating. When the speed is low, aerodynamic heating plays a major role, but as the speed increases, radiation heating gradually becomes more obvious. When the reentry vehicle re-enters the atmosphere at high speed, the high-temperature shock wave layer at the head passes backwards, causing radiation heating to the protective cover. In this way, the thermal protection layer is simultaneously subjected to aerodynamic convection heating and radiation heating, and the ratio of the heat flow rates of the two varies with the speed and altitude of the spacecraft. The return capsule of an interstellar probe enters the Earth's atmosphere at the second cosmic speed, and the radiation heating in the local orbital segment can account for more than one-third of the total heating. Radiant heat can not only lead to the decomposition of heat inside the protective material, but can also pass through the protective material and be conducted to the interior of the spacecraft, affecting the safety of instruments and personnel.

[0003] Therefore, it is of great significance to conduct thermal insulation assessment research on hypersonic vehicle structures and materials, and develop a coupled heating device of plasma aerodynamic heat flux and radiation heat flux to conduct ground assessment tests of composite thermal protection materials in the field of aerospace aerodynamic heat, which is of great significance to the development of deep space exploration, interstellar travel and hypersonic weapons strategy. Summary of the invention

[0004] The object of the present invention is to provide a plasma pneumatic heating and radiation heating coupled heating device, which can simulate the thermal environment to which the thermal protection layer of a spacecraft is subjected during flight;

[0005] The present invention provides a plasma pneumatic heating and radiation heating coupling heating device, characterized in that it comprises:

[0006] A first heat reflection mechanism is arranged at a place of use;

[0007] The second heat reflection mechanism is symmetrically arranged with the first heat reflection mechanism;

[0008] The plasma heating device is arranged between the first heat reflecting mechanism and the second heat reflecting mechanism and is located close to the first heat reflecting mechanism;

[0009] The radiation heating device is arranged between the plasma heating device and the second heat reflecting mechanism.

[0010] According to another embodiment, the first heat reflecting mechanism and the second heat reflecting mechanism are respectively a first concave mirror and a second concave mirror;

[0011] There is a focus of the first concave mirror between the plasma heating device and the radiation heating device.

[0012] According to a further embodiment, the focal points of the first concave mirror and the second concave mirror are located on a center line of the plasma heating device.

[0013] According to another embodiment, a grid baffle for adjusting light transmittance is further included, and the grid baffle is located between the focus and the radiation heating device.

[0014] According to further embodiments, the grille baffle comprises:

[0015] A bracket is provided at the place of use;

[0016] The light beam adjustment mechanism is arranged on the bracket.

[0017] According to another embodiment, the light beam adjustment mechanism comprises:

[0018] A driving mechanism connected to the bracket;

[0019] A plurality of fan blade shafts have one end rotatably connected to the driving mechanism and the other end rotatably connected to the outer frame.

[0020] According to another embodiment, the drive mechanism comprises:

[0021] The motor is installed at the place of use;

[0022] A rotating shaft is connected to the motor, and a plurality of transmission grooves are arranged along the radial direction of the rotating shaft;

[0023] A plurality of cranks, each having a protrusion matched with the transmission groove;

[0024] The inner frame is sleeved on the rotating shaft and is rotatably connected to the rotating shaft; the inner frame is provided with a plurality of through holes along the radial direction, and a plurality of cranks are rotatably connected to the inner frame through the through holes;

[0025] Among them, the fan blade shaft is arranged along the radial direction of the inner frame, one end of the fan blade shaft is connected to the crank handle at the through hole position, and the other end of the fan blade shaft is connected to the outer frame.

[0026] According to other embodiments, the plasma heating device is a DC arc plasma generator, an AC arc plasma generator, a high frequency plasma generator or a gas stream heater.

[0027] According to a further embodiment, the radiant heating device is a point light source.

[0028] According to further embodiments, the point light source is a quartz lamp, an electrically heated carbon rod or an arc lamp.

[0029] Beneficial effects:

[0030] Technical effects:

[0031] The present invention is provided with a first heat reflecting mechanism, a second heat reflecting mechanism, a plasma heating device and a radiation heating device; the second heat reflecting mechanism is symmetrically arranged with the first heat reflecting mechanism; the plasma heating device is arranged between the first heat reflecting mechanism and the second heat reflecting mechanism and is located near the first heat reflecting mechanism; the radiation heating device is arranged between the plasma heating device and the second heat reflecting mechanism; compared with the prior art, by using a plasma heater to provide an aerodynamic heat source for a sample, since the sample is close to the plasma heater and is located at the focus of the first heat reflecting mechanism at the same time; the radiation heater is located at the focus of the second heat reflecting mechanism, the radiation heater generates a radiation heat flow which is reflected to the first heat reflecting mechanism through the second heat reflecting mechanism, and the first heat reflecting mechanism then reflects the radiation heat flow and concentrates it on the surface of the sample, thereby realizing convection and radiation coupled heating of the sample, so as to simulate the thermal environment to which the thermal protection layer of the aerospace vehicle is subjected during flight, and then complete the heat insulation assessment of the structure and materials of the hypersonic vehicle, and finally avoid the problem that the internal instruments of the aerospace vehicle cannot work normally and the safety of personnel can not be caused by the internal thermal decomposition of the thermal protection layer of the aerospace vehicle during actual high-speed flight.

[0032] Social effect: The present invention is provided with a first heat reflecting mechanism, a second heat reflecting mechanism, a plasma heating device and a radiation heating device; the second heat reflecting mechanism is symmetrically arranged with the first heat reflecting mechanism; the plasma heating device is arranged between the first heat reflecting mechanism and the second heat reflecting mechanism and is located close to the first heat reflecting mechanism; the radiation heating device is arranged between the plasma heating device and the second heat reflecting mechanism; compared with the prior art, the present invention can promote the development of my country's aerospace technology field, and has important significance for the structure and materials of hypersonic aircraft in the development of deep space exploration, interstellar travel and hypersonic weapon strategy. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] 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.

[0034] Figure 1 A schematic diagram of the principle of a coupled heating device for plasma pneumatic heating and radiation heating provided by the present invention;

[0035] Figure 2 This is a schematic diagram of the main view of the grille baffle structure of the present invention;

[0036] Figure 3 It is a schematic diagram of the structure of the light beam adjustment mechanism of a fan blade shaft in the present invention in the southwest isometric direction;

[0037] Figure 4 It is a schematic diagram of the structure of a beam adjustment mechanism of a blade shaft in a side view of the present invention;

[0038] Figure 5 It is a schematic diagram of the main view direction structure of a light beam adjustment mechanism of a fan blade shaft in the present invention;

[0039] Figure 6 It is a schematic diagram of the structure of a beam adjustment mechanism of a blade shaft in a top view in the present invention;

[0040] Figure 7 for Figure 6 Cross-sectional view along the AA direction.

[0041] Description of reference numerals:

[0042] 1. The first heat reflection mechanism;

[0043] 2. Second heat reflection mechanism;

[0044] 3. Plasma heating equipment;

[0045] 4. Radiant heating equipment;

[0046] 5. Focus;

[0047] 6. Grille baffle; 61. Bracket; 62. Light beam adjustment mechanism; 621. Driving mechanism; 6211. Motor; 6212. Rotating shaft; 62121. Transmission groove; 6213. Crank handle; 62131. Protrusion; 6214. Inner frame; 62141. Through hole; 622. Fan blade shaft; 623. Outer frame. DETAILED DESCRIPTION

[0048] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than 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.

[0049] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0050] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, 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 connection of two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0051] like Figures 1 to 7 As shown, the present invention provides a coupled heating device of plasma pneumatic heating and radiation heating, comprising a first heat reflecting mechanism 1, a second heat reflecting mechanism 2, a plasma heating device 3 and a radiation heating device 4, wherein the first heat reflecting mechanism 1 is arranged at the place of use; in actual use, the first heat reflecting mechanism 1 serves to receive the radiant heat reflected by the second heat reflecting mechanism 2 and to concentrate the radiant heat and reflect it to the surface of the sample, thereby realizing convection and radiation coupled heating of the sample.

[0052] The second heat reflection mechanism 2 is symmetrically arranged with the first heat reflection mechanism 1; in actual use, the second heat reflection mechanism 2 is arranged to facilitate subsequent heat coupling;

[0053] The plasma heating device 3 is arranged between the first heat reflecting mechanism 1 and the second heat reflecting mechanism 2, and is located near the first heat reflecting mechanism 1. In actual use, the sample is placed at a position where the radiation heating device 4 is close to the plasma heating device 3, so that the plasma heating device 3 heats the sample and facilitates subsequent heat coupling.

[0054] The radiation heating device 4 is arranged between the plasma heating device 3 and the second heat reflecting mechanism 2; in actual use, the radiation heating device 4 is arranged to provide the pneumatic heat source to the sample;

[0055] Specifically, the first heat reflecting mechanism 1 and the second heat reflecting mechanism 2 are respectively the first concave mirror and the second concave mirror, and the focus 5 of the first concave mirror is located between the plasma heating device 3 and the radiation heating device 4; in actual use, since the concave mirror has a focusing effect, the sample is arranged at the focus 5 of the first concave mirror through the arrangement of the first concave mirror and the second concave mirror to achieve the above-mentioned heat coupling; as an optional embodiment, the outer edge diameter of the first concave mirror is 3.0m, and the spherical crown radius is 4m; the outer edge diameter of the second concave mirror is consistent with that of the first concave mirror, both of which are 3m, and the spherical crown radius is 3m, the axes of the first concave mirror and the second concave mirror coincide, and the focal points of the two are 3.5m apart; however, it should be understood that the above-mentioned heat coupling effect can also be achieved by other suitable methods and devices;

[0056] It should be noted that, as an optional implementation, the reflective mirror surfaces of the first concave mirror and the second concave mirror may be made of silver-plated or aluminum-plated glass. Of course, they may also be mirror surfaces made of other materials such as aluminum polishing or polyester film aluminum plating.

[0057] The focal points of the first concave mirror and the second concave mirror both fall on the center line of the plasma heating device 3. In actual use, the above arrangement can reduce the heat loss of the radiation heater by the first heat reflection mechanism 1 and the second heat reflection mechanism 2, so as to achieve a better coupled heating effect on the sample.

[0058] In addition, in order to adjust the radiation heat flux penetration rate to achieve the effect of adjusting the radiation heat flux density on the surface of the sample, the plasma pneumatic heating and radiation heating coupling heating device provided by the present invention also includes a grid baffle, which is used to adjust the transmittance, and the grid baffle is located between the focus 5 and the radiation heating device 4; wherein,

[0059] The grille baffle 6 includes a bracket 61 and a beam adjustment mechanism 62. The bracket 61 is arranged at the place of use; the beam adjustment mechanism 62 is arranged on the bracket 61; in actual use, the bracket 61 plays the role of supporting the beam adjustment mechanism 62 to facilitate the placement of the beam adjustment mechanism 62;

[0060] Specifically, the beam adjustment mechanism 62 includes a driving mechanism 621, a plurality of blade shafts 622 and an outer frame 623. The driving mechanism 621 is connected to the bracket 61; the plurality of blade shafts 622 ( Figure 212 blade shafts 622 are shown in the figure, one end of which is rotatably connected to the driving mechanism 621, and the other end is rotatably connected to the outer frame 623; in actual use, the driving mechanism 621 is used to drive the blade shaft 622 to rotate, so as to adjust the opening and closing of the blades, thereby achieving the above-mentioned light transmittance adjustment;

[0061] Then, the driving mechanism 621 includes a motor 6211, a rotating shaft 6212, a plurality of cranks 6213 and an inner frame 6214; the motor 6211 is arranged at the place of use; the rotating shaft 6212 is connected to the motor 6211, and the rotating shaft 6212 is provided with a plurality of transmission grooves 62121 in the radial direction; a plurality of cranks 6213 have protrusions 62131 adapted to the transmission grooves 62121; the inner frame 6214 is sleeved on the rotating shaft 6212 and is rotatably connected to the rotating shaft 6212; the inner frame 6214 is provided with a plurality of through holes 62141 in the radial direction, and a plurality of cranks 6213 are rotatably connected to the inner frame 6214 through the through holes 62141; wherein the fan blade shaft 622 is arranged along the radial direction of the inner frame 6214, one end of the fan blade shaft 622 is connected to the crank 6213 at the position of the through hole 62141, and the other end of the fan blade shaft 622 is connected to the outer frame 623 In actual use, the motor 6211 is preferably a stepper motor 6211, so as to accurately control the opening and closing angle of the fan blades, and thus more accurately adjust the light transmittance; specifically, the motor 6211 is connected to the shaft 6212, and when the motor 6211 rotates, the shaft 6212 is driven to rotate, and when the shaft 6212 rotates, the protrusion 62131 adapted to the transmission groove 62121 is driven to rotate. Since a plurality of cranks 6213 are rotatably connected to the inner frame 6214 through the through hole 62141, and the fan blade shaft 622 is connected to the crank 6213 at the position of the through hole 62141, when the protrusion 62131 rotates, the fan blade shaft 622 can be driven to rotate, thereby completing the opening and closing of the fan blades; according to the present invention, the driving mechanism 621 can also be of other suitable types, as long as the above-mentioned light transmittance adjustment can be achieved; wherein,

[0062] The plasma heating device 3 is a DC arc plasma generator, an AC arc plasma generator, a high-frequency plasma generator or a gas stream heater; it should be understood that the DC arc plasma generator, the AC arc plasma generator, the high-frequency plasma generator or the gas stream heater is only preferred;

[0063] It should be noted that, as an optional embodiment, the power of the plasma heater is 50KW-1MW; specifically, in actual use, a 1MW-level pneumatic heater can be used as the above-mentioned high-frequency plasma generator, and powered by a high-frequency power supply, so that the generated high-temperature ionized gas is pneumatically heated to the sample after being ejected;

[0064] Specifically, the radiation heating device 4 is a point light source; in actual use, using the radiation heating device 4 as a point light source can reduce the loss of heat reflected by the first heat reflection mechanism 1 and the second heat reflection mechanism 2, thereby making the heat more concentrated for reflection to better achieve the above coupling;

[0065] Then, the point light source is a quartz lamp, an electrically heated carbon rod or an arc lamp; it should be noted that the quartz lamp, the electrically heated carbon rod or the arc lamp are existing and will not be described in detail here to save space.

[0066] It should be noted that, as an optional implementation, the power of the radiation heating device 4 is 5KW-500KW;

[0067] The present invention utilizes a plasma heater to provide an aerodynamic heat source for a sample. Since the sample is close to the plasma heater, the sample can be heated by plasma startup. At the same time, the sample is arranged at the focus of a first heat reflection mechanism to facilitate subsequent radiation heating. The radiation heater is located at the focus of a second heat reflection mechanism. The radiation heater generates a radiation heat flow that is reflected to the first heat reflection mechanism through the second heat reflection mechanism. The first heat reflection mechanism then reflects the radiation heat flow and concentrates it on the surface of the sample, thereby realizing convection and radiation coupled heating of the sample, so as to simulate the thermal environment that the thermal protection layer of the aerospace vehicle is subjected to during flight, and further complete the heat insulation assessment of the structure and materials of the hypersonic vehicle, and finally avoid the problem that the internal instruments of the aerospace vehicle cannot work normally and the safety of personnel cannot occur due to the internal thermal decomposition of the thermal protection layer of the aerospace vehicle during actual high-speed flight.

[0068] It should be noted that, in the present invention, the sample refers to the hypersonic vehicle structure and material to be tested, which is set at the focus 5 when in use.

[0069] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A coupled heating device for plasma pneumatic heating and radiation heating, characterized in that: include: A first heat reflection mechanism (1) is arranged at a place of use; A second heat reflection mechanism (2) is arranged symmetrically with the first heat reflection mechanism (1); A plasma heating device (3) is arranged between the first heat reflecting mechanism (1) and the second heat reflecting mechanism (2), and is located close to the first heat reflecting mechanism (1); A radiation heating device (4) is arranged between the plasma heating device (3) and the second heat reflecting mechanism (2); The first heat reflection mechanism (1) and the second heat reflection mechanism (2) are respectively a first concave mirror and a second concave mirror; Wherein, a focus (5) of the first concave mirror is provided between the plasma heating device (3) and the radiation heating device (4); The focal points (5) of the first concave mirror and the second concave mirror are located on the center line of the plasma heating device (3).

2. The plasma pneumatic heating and radiation heating coupling heating device according to claim 1 is characterized in that: It also includes a grille baffle (6) for adjusting light transmittance, wherein the grille baffle (6) is located between the focus (5) and the radiation heating device (4).

3. The plasma pneumatic heating and radiation heating coupling heating device according to claim 2 is characterized in that: The grille baffle (6) comprises: A bracket (61) is arranged at a place of use; The light beam adjustment mechanism (62) is arranged on the bracket (61).

4. The plasma pneumatic heating and radiation heating coupling heating device according to claim 3 is characterized in that: The light beam adjustment mechanism (62) comprises: A driving mechanism (621) connected to the support (61); A plurality of fan blade shafts (622) are rotatably connected to the driving mechanism (621) at one end and rotatably connected to the outer frame (623) at the other end.

5. The plasma pneumatic heating and radiation heating coupling heating device according to claim 4, characterized in that: The driving mechanism (621) comprises: A motor (6211) is arranged at a place of use; A rotating shaft (6212) connected to the motor (6211), wherein the rotating shaft (6212) is provided with a plurality of transmission grooves (62121) along a radial direction; A plurality of crank handles (6213) having protrusions (62131) adapted to the transmission grooves (62121); The inner frame (6214) is sleeved on the rotating shaft (6212) and is rotatably connected to the rotating shaft (6212); the inner frame (6214) is provided with a plurality of through holes (62141) along the radial direction, and a plurality of cranks (6213) are rotatably connected to the inner frame (6214) through the through holes (62141); Wherein, the fan blade shaft (622) is arranged along the radial direction of the inner frame (6214), one end of the fan blade shaft (622) is connected to the crank (6213) at the position of the through hole (62141), and the other end of the fan blade shaft (622) is connected to the outer frame (623).

6. The plasma pneumatic heating and radiation heating coupling heating device according to claim 1, characterized in that: The plasma heating device (3) is a DC arc plasma generator, an AC arc plasma generator, a high-frequency plasma generator or a fuel gas flow heater.

7. The plasma pneumatic heating and radiation heating coupling heating device according to claim 1 is characterized in that: The radiation heating device (4) is a point light source.

8. The plasma pneumatic heating and radiation heating coupling heating device according to claim 7, characterized in that: The point light source is a quartz lamp, an electrically heated carbon rod or an arc lamp.

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