Air inlet ring, heater and spacecraft pneumatic heatproof ground test equipment

Abstract

The utility model relates to the technical field of spacecraft pneumatic heatproof ground test equipment, in particular to an air inlet ring, a heater and spacecraft pneumatic heatproof ground test equipment. The air inlet ring comprises a ring body, the two end faces of the ring body in the axial direction follow the shape of equipment faces located at the two ends of the air inlet ring, the section, with the largest thickness, of the ring body in the radial direction is located on the peripheral section away from the center of the ring body, and the two end faces of the ring body in the axial direction are each provided with a sealing groove used for installing a sealing ring. A plurality of air distribution holes are formed in the circumferential direction of the ring body at intervals and penetrate from the outer circumferential side face of the ring body to the inner side face of the ring body to supply air to the heater. The two end faces of the air inlet ring are matched with the connected equipment face in a shape follow-up mode, the fit clearance can be made to be as small as possible, impurity particles are prevented from entering the air inlet ring, sealing rings are arranged in the sealing grooves in the two end faces, the sealing performance between the air inlet ring and the connected equipment is improved, and the sealing structure is simple and easy to achieve. And meanwhile, impurity particles can be further prevented from entering deeper positions along the fit clearance.

Description

TECHNICAL FIELD

[0001] The utility model relates to spacecraft aerodynamic heat protection ground test equipment technical field especially, relates to a kind of air inlet ring, heater and spacecraft aerodynamic heat protection ground test equipment. BACKGROUND

[0002] When ground heat protection test is carried out using spacecraft aerodynamic heat protection ground test equipment, air inlet ring needs to be used for air flow input and distribution, and equipment on both sides of air inlet ring is insulated, air inlet ring contacts high-temperature airflow in use process, so air inlet ring needs to have good insulation performance, can also resist 300 DEG C or above high temperature and have certain strength, after years of development and use experience, air inlet ring material gradually solidifies as ceramic, but the axial section of existing ceramic air inlet ring is mainly regular "T" type or rectangle, in use, air inlet ring both sides are easy to leak, not conducive to air flow control, and because the equipment surface shape connected with air inlet ring both sides is irregular, leading to the gap between air inlet ring and connected equipment, impurity particles are easy to remain in the gap. SUMMARY

[0003] The utility model discloses a kind of air inlet ring of spacecraft aerodynamic heat protection ground test equipment heater, heater including the air inlet ring and spacecraft aerodynamic heat protection ground test equipment including the heater, solve the problem that existing air inlet ring side is easy to leak and import impurity.

[0004] To achieve the above object, first, the utility model provides a kind of air inlet ring of spacecraft aerodynamic heat protection ground test equipment heater, including ring body, two end faces of ring body in axial direction are with the equipment surface located in the both ends of air inlet ring along shape, and the section of ring body in radial direction maximum thickness is located in the outer peripheral section away from the center of ring body, two end faces of ring body in axial direction are respectively equipped with the sealing groove for installing sealing ring;

[0005] Multiple gas distribution holes are arranged at intervals in the circumferential direction of the ring body, and the gas distribution holes pass through from the outer peripheral side surface of the ring body to the inner side surface of the ring body.

[0006] Optionally, the sealing groove is located in the outer peripheral section.

[0007] Optionally, the maximum gap between the two end faces of the ring body in the axial direction and the adjacent equipment surface is not greater than 2 mm.

[0008] Optionally, the gas distribution hole is located at one end of the inner side surface of the ring body and is arranged at the center of the inner side surface of the ring body in the axial direction.

[0009] Optionally, the material of the ring body is ceramic.

[0010] Optionally, the ring body is made by 3D printing.

[0011] In a second aspect, the utility model also provides a kind of heater, including the air inlet ring of any implementation in the first aspect.

[0012] In a third aspect, the utility model also provides a kind of spacecraft aerodynamic heat protection ground test equipment, including the heater of any implementation in the second aspect.

[0013] The above technical solution of the utility model has the following advantages:

[0014] The air inlet ring provided by the utility model is used for spacecraft aerodynamic heat protection ground test equipment heater, including ring body, the two end faces of ring body in axial direction are conformal with the equipment face located at the two ends of air inlet ring, and the outer peripheral section of ring body in radial direction maximum thickness is located away from the center of ring body, the two end faces of ring body in axial direction are respectively provided with sealing groove for installing sealing ring, a plurality of gas distribution holes are arranged at interval in the circumferential direction of ring body, gas distribution hole is penetrated from the outer peripheral side surface of ring body to the inner side surface of ring body, and is used for supplying gas to spacecraft aerodynamic heat protection ground test equipment heater.The two end faces of the air inlet ring are conformal with the equipment face connected, can make the cooperation gap as small as possible, prevent impurity particles from entering, and sealing ring is arranged in the sealing groove of two end faces, the sealing performance between air inlet ring and connected equipment is increased, and the sealing structure is simple, and is relatively easy to realize.At the same time, impurity particles can be further prevented from entering deeper along the cooperation gap. BRIEF DESCRIPTION OF DRAWINGS

[0015] The utility model drawing is only provided for the purpose of illustration, and the proportion and quantity of each component in the drawing may not be consistent with the actual product.

[0016] Figure 1 It is the structure schematic view of air inlet ring in the embodiment of the utility model;

[0017] Figure 2 It is Figure 1 The axial view schematic view of air inlet ring in;

[0018] Figure 3 It is Figure 2 The A-A section schematic view of air inlet ring in;

[0019] Figure 4 It is Figure 3 The B part enlarged schematic view of air inlet ring in;

[0020] Figure 5 It is the section schematic view of air inlet ring installed in two end equipment in the embodiment of the utility model;

[0021] Figure 6 It is Figure 5 The C part enlarged schematic view in;

[0022] In the drawing:

[0023] 1: air inlet ring;

[0024] 11: ring body;

[0025] 111: sealing groove;

[0026] 112: air distribution hole;

[0027] 12: sealing ring;

[0028] 2: device. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely described below in combination with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the protection scope of the utility model.

[0030] As shown in Figures 1-4 The air inlet ring 1 provided by the embodiments of the utility model comprises a ring body 11, which is used for the heater of a spacecraft aerodynamic heat protection ground test device. Wherein, the two end faces of the ring body 11 in the axial direction are conformal with the device faces located at the two ends of the air inlet ring 1, that is, the shape of the two end faces of the air inlet ring 1 in the axial direction changes with the change of the external shape of the device matched therewith, so that the matching gap between the air inlet ring 1 and the device is controlled within a very small range. Since the two end faces of the ring body 11 in the axial direction are conformal, the ring body can be divided into multiple sections in the radial direction, and the two adjacent sections can be at a certain angle or have a certain curvature. In addition, the multiple sections can also have different thicknesses. In order to avoid impurity particles from entering the matching gap as much as possible, preferably, the section with the maximum thickness of the ring body 11 in the radial direction is located at the outer peripheral section away from the center of the ring body, that is, the outermost section in the radial direction of the ring body 11. Further preferably, the ring body 11 is provided with a sealing groove 111 for installing a sealing ring 12 on each of the two end faces in the axial direction.

[0031] As shown in Figure 1 , Figure 3 and Figure 4 A plurality of air distribution holes 112 are arranged at intervals in the circumferential direction of the ring body 11, the air distribution holes 112 penetrate from the outer peripheral side surface of the ring body 11 to the inner side surface of the ring body 11, and are used for supplying air to the heater of the spacecraft aerodynamic heat protection ground test device.

[0032] As shown in Figure 5 and Figure 6As shown, in use, the air inlet ring 1 is installed between the two sides of the equipment 2, the two end faces are matched with the two sides of the equipment face, the matching gap is as small as possible, and the air supply hole 112 supplies air to the spacecraft aerodynamic heat protection ground test equipment heater. The sealing groove 111 is provided with a sealing ring 12, which is tightly attached to the equipment face, which can increase the sealing performance between the air inlet ring and the connected equipment, and the sealing structure is simple and easy to realize. On the other hand, it prevents impurity particles from entering deeper along the matching gap.

[0033] In an example, referring to Figure 2 and Figure 4 As shown, the sealing groove 111 is located on the outer peripheral section, which can better prevent impurity particles from entering deeper along the matching gap.

[0034] In this embodiment, preferably, the maximum of the matching gap between the two end faces of the ring body 11 in the axial direction and the adjacent equipment face is not greater than 1mm.

[0035] In this embodiment, preferably, the air supply hole 112 is located at one end of the inner side surface of the ring body and is centrally arranged on the inner side surface of the ring body in the axial direction.

[0036] In this embodiment, the material of the ring body 11 can be any material that is insulating and has strength and high temperature resistance performance that meets the use requirements, for example, polyimide, ceramic, etc. Preferably, the material of the ring body 11 is ceramic.

[0037] In order to reduce the molding difficulty and improve the yield, preferably, the ring body 11 in this embodiment is made by 3D printing.

[0038] This embodiment also provides a heater for a spacecraft aerodynamic heat protection ground test equipment, which can use any of the above air inlet rings.

[0039] This embodiment also provides a spacecraft aerodynamic heat protection ground test equipment, which can use any of the above heaters.

[0040] It should be noted that the air flow required for the operation of the heater can be increased or decreased according to the total air flow demand, and the diameter and number of the air supply holes can be increased or decreased, which will not be described here.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, and are not limited thereto; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that not every embodiment contains only one independent technical solution, and in the absence of scheme conflict, each technical feature mentioned in each embodiment can be combined in any way to form other embodiments that can be understood by those skilled in the art.

[0042] Furthermore, the technical solutions described in the foregoing embodiments are modified, or some of the technical features are replaced equivalently without departing from the scope of the present application, and the essence of the corresponding technical solutions does not deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. An air inlet ring comprising a ring body, characterized in that: two end faces of the ring body in the axial direction are conformal to the device faces at the two ends of the air inlet ring, and the ring body has a maximum thickness in the radial direction at an outer peripheral section away from the center of the ring body, and the ring body is provided with a sealing groove for mounting a sealing ring on each of the two end faces in the axial direction; a plurality of gas distribution holes are provided at intervals in the circumferential direction of the ring body, and the gas distribution holes are penetrated by the outer peripheral side surface of the ring body to the inner side surface of the ring body.

2. The gas inlet ring of claim 1, wherein: The sealing groove is located at the outer peripheral section.

3. The gas inlet ring of claim 1, wherein: The maximum gap between the two end faces of the ring body in the axial direction and the adjacent device faces is not greater than 1 mm.

4. The gas inlet ring of claim 1, wherein: The gas distribution hole located at one end of the inner side surface of the ring body is arranged at the center of the inner side surface of the ring body in the axial direction.

5. The gas inlet ring of claim 1, wherein: The material of the ring body is ceramic.

6. The gas inlet ring of claim 1 or 5, wherein: The ring body is made by 3D printing.

7. A heater characterized by: An air inlet ring according to any one of claims 1 to 6.

8. A spacecraft aerodynamic heat shield ground test apparatus, characterized by: A heater according to claim 7.

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