CN109436373B - High-ultrasonic rapid force and heat combined test cabin - Google Patents

Abstract

A high-ultrasonic-speed force-heat combined test cabin body is formed by taking a double-layer cylindrical sleeve as a structural main body of the test cabin body, wherein a test environment is provided for force-heat combined test in the cylindrical sleeve, a cooling water circulation channel is formed in an interlayer of the double-layer cylindrical sleeve and is used for circularly cooling the test cabin body, a cabin door is positioned at the front end of the cabin body, a tensile force model carrying frame of the high-ultrasonic-speed force-heat combined test is conveniently placed, a test model is conveniently installed and removed, and external equipment on the upper portion and the lower portion of the cabin body can effectively isolate vibration conduction of the test model in a test process. The invention ensures the smooth development of the high ultrasonic speed force heat combined test, runs stably for a long time, and has the advantages of reasonable structure, easy processing, convenient installation, convenient test operation and the like.

Description

A hypersonic combined force and heat test chamber

Technical Field

The invention belongs to hypersonic test technology and relates to a cabin suitable for hypersonic force and heat combined test.

Background technique

Hypersonic tests use heaters and nozzles to heat and accelerate the airflow, simulating the local thermal environment of the hypersonic aircraft in the test chamber to study the thermal performance of the hypersonic aircraft's thermal protection materials and structures under aerodynamic conditions. In fact, hypersonic aircraft are also subject to a variety of harsh factors such as aerodynamic loads and surface oxidation during flight. Hypersonic combined force and heat tests are one of the important ground test methods for studying the high temperature, stress, oxidation and other problems of the nose cone, wing leading edge and other parts of new hypersonic aircraft during long-term high-speed flight. It plays an important role in promoting the design of aircraft thermal protection systems. The test chamber is one of the important components of the arc wind tunnel test equipment. It is an important site for disassembling test models and conducting assessment tests. It has the important mission of maintaining the low-pressure and long-term stable operation of the test environment.

Since the combined force and heat test needs to simulate the mechanical loading of the model to be tested, long-term hypersonic aerodynamic ablation and oxygen partial pressure environment, the design of the test cabin needs to meet multiple complex requirements such as vacuum, high temperature, long-term operation and coordination of various subsystems. At the same time, it is also necessary to take into account the disassembly and assembly of the model, observation of the test process, and test data collection, so as to ensure the reliable and stable operation of the test equipment and obtain real and effective test data. The traditional hypersonic test cabin is a cubic structure with two doors on the left and right, and a circular observation window on each door. Since the front and rear ends of the test cabin are connected to arc wind tunnel equipment, when the traditional hypersonic test cabin is used in the combined force and heat test, the load-bearing frame of the tensile prototype used to achieve tensile loading will hinder the opening and closing of the door and affect the disassembly and assembly of the model. The tensile loading mechanism of the prototype will also cause vacuum leakage in the traditional cabin.

Summary of the invention

The technology of the present invention solves the problem of overcoming the shortcomings of traditional hypersonic test chambers in conducting combined force and heat tests, and providing a test chamber that is convenient for model assembly and disassembly, convenient for data collection and acquisition, and suitable for conducting combined force and heat tests of hypersonic speed.

The technical solution of the present invention is as follows: a hypersonic combined force and heat test cabin, comprising a double-layer cylindrical sleeve, a cooling ring, a front flange, a rear flange, a rectangular observation window, a tension loading window, a bellows, a front cabin door, a nozzle interface, and a circular observation window; two cooling rings are respectively butted with the two ends of the outer sleeve of the double-layer cylindrical sleeve, the front flange is butted with the inner sleeve of the double-layer cylindrical sleeve and a cooling ring, and the rear flange is butted with the inner sleeve of the double-layer cylindrical sleeve and a cooling ring; two rectangular observation windows are respectively installed on the left and right sides of the double-layer cylindrical sleeve, two tension loading windows are respectively installed on the upper and lower sides of the cylindrical sleeve, and the bellows is butted with the tension loading window; the front cabin door is butted with the front flange, and the opening and closing of the front cabin door are realized by hinges and door locks.

The double-layer cylindrical sleeve is welded with the cooling ring, the front flange, the rear flange, the rectangular observation window and the tension loading window by using argon arc welding.

A sealing groove is provided on the tension loading window, and a rubber ring is used for sealing when the window is butted against the corrugated pipe.

The rectangular observation window and the circular observation window are provided with sealing grooves, which are covered with quartz glass and sealed with rubber rings.

The front door and the front flange are installed in a snap-fit manner, and a rubber sealing ring is bonded to the snap of the front door.

The inner sleeve of the double-layer cylindrical sleeve is 520 mm long, 490 mm in inner diameter and 6 mm in wall thickness, while the outer sleeve is 406 mm long, 508 mm in inner diameter and 6 mm in wall thickness.

The cooling ring has a maximum inner diameter of 570 mm and a wall thickness of 6 mm.

The cooling ring has four cooling water interfaces evenly distributed thereon.

The front door is a disc with a diameter of 680mm, a wall thickness of 15mm, and a nozzle interface in the center.

The nozzle interface has an inner diameter of 140 mm, and two circular observation windows with a diameter of 150 mm are evenly distributed at a distance of 400 mm on the left and right.

The rectangular observation window is 280mm long, 80mm wide, and extends 50mm outside the cabin. The corners are rounded to relieve stress.

The inner diameter of the tension loading window is 100mm.

The bellows is 200mm long, 100mm inside diameter, and has a maximum expansion and contraction range of ±30mm.

Compared with the traditional test chamber, the advantages of the present invention are:

(1) The structure of the present invention is sophisticated. The entire cabin can be cooled by water through two front and rear cooling loops to ensure long-term operation of the test. The internally enclosed structure ensures the vacuum test environment required for the combined force and heat test.

(2) The structural form of the front door of the present invention provides ample space for the tensile prototype, making it convenient for the model to be disassembled and assembled.

(3) The bellows of the present invention can effectively prevent the vibration of the equipment from being transmitted to the model through the tension mechanism during the test, and the upper cover of the bellows provides an interface for the oxygen partial pressure system and the test system.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic structural diagram of the present invention.

Detailed ways

As shown in Figure 1, the combined force and heat test chamber includes a double-layer cylindrical sleeve 1, a cooling ring 2, a front flange 3, a rear flange 4, a front cabin door 5, a rectangular observation window 6, a tension loading window 7, a bellows 8, a nozzle interface 9, and a circular observation window 10. The two ends of the outer sleeve of the double-layer cylindrical sleeve 1 are connected to the two cooling rings 2, the front flange 3 is connected to the inner sleeve of the double-layer cylindrical sleeve 1 and the cooling ring 2, and the rear flange is connected to the inner sleeve of the double-layer cylindrical sleeve 1 and the cooling ring 2; the two rectangular observation windows 6 are located on the left and right sides of the double-layer cylindrical sleeve 1, the two tension loading windows 7 are located on the upper and lower sides of the cylindrical sleeve, the bellows 8 is connected to the tension loading window 7, and the front cabin door 5 is connected to the front flange 3. The hatch door can be opened and closed by hinges and door locks.

The inner sleeve of the double-layer cylindrical sleeve 1 is 520mm long, 490mm in diameter, and 6mm thick. The outer sleeve is 406mm long, 508mm in diameter, and 6mm thick. The maximum inner diameter of the cooling ring 2 is 570mm, and the wall thickness is 6mm. There are 4 evenly distributed cooling water interfaces, and the front and rear cooling rings have four inlets and four outlets. The front door is a disc with a diameter of 680mm and a wall thickness of 15mm. The center position is the nozzle interface 9, and the nozzle interface 9 has an inner diameter of 140mm. Two circular observation windows 10 are evenly distributed at a distance of 400mm from left to right. The circular observation window 10 has an inner diameter of 150mm. The rectangular observation window 6 is 280mm long, 80mm wide, and extends 50mm outside the cabin to effectively prevent the quartz glass on the window from being burned during long-term testing. The corners are rounded to release stress. The inner diameter of the tensile loading window 7 is 100mm, and the bellows 8 is 200mm long, 100mm in diameter, and the maximum telescopic amount is ±30mm.

Claims (8)

1. A hypersonic thermal combined test cabin, characterized in that it comprises a double-layer cylindrical sleeve (1), a cooling ring (2), a front flange (3), a rear flange (4), a rectangular observation window (6), a tension loading window (7), a bellows (8), a front cabin door (5), a nozzle interface (9), and a circular observation window (10); two cooling rings (2) are respectively connected to the two ends of the outer sleeve of the double-layer cylindrical sleeve (1); the front flange (3) is connected to the inner sleeve of the double-layer cylindrical sleeve (1) and a cooling ring (2); the rear flange (4) is connected to the inner sleeve of the double-layer cylindrical sleeve (1) and a cooling ring (2); two rectangular observation windows (6) are respectively installed on the left and right sides of the double-layer cylindrical sleeve (1); two tension loading windows (7) are respectively installed on the upper and lower sides of the cylindrical sleeve (1); the bellows (8) is connected to the tension loading window (7); the front cabin door (5) is connected to the front flange (3), and the front cabin door (5) is opened and closed by hinges and door locks; The tensile loading window (7) is provided with a sealing groove, and a rubber ring is used to seal when it is connected to the bellows (8); The rectangular observation window (6) and the circular observation window (10) are provided with sealing grooves, which are covered with quartz glass and sealed with rubber rings. 2. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that the double-layer cylindrical sleeve (1) and the cooling ring (2), the front flange (3), the rear flange (4), the rectangular observation window (6), and the tensile loading window (7) are welded using argon arc welding. 3. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the front door (5) and the front flange (3) are installed in a snap-fit manner, and a rubber sealing ring is bonded to the snap of the front door (5). 4. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that the inner sleeve of the double-layer cylindrical sleeve (1) is 520 mm long, 490 mm inner diameter, and 6 mm thick, while the outer sleeve is 406 mm long, 508 mm inner diameter, and 6 mm thick. 5. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the maximum inner diameter of the cooling ring (2) is 570 mm and the wall thickness is 6 mm; the cooling ring (2) has 4 cooling water interfaces evenly distributed. 6. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the front door (3) is a disc with a diameter of 680 mm, a wall thickness of 15 mm, and a nozzle interface (9) is opened at the center. 7. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the rectangular observation window (6) is 280 mm long, 80 mm wide, and extends 50 mm outside the chamber, and the corners are rounded to release stress. 8. A hypersonic combined mechanical and thermal test chamber according to claim 1, characterized in that: the nozzle interface (9) has an inner diameter of 140 mm, and two circular observation windows (10) with a diameter of 150 mm are evenly distributed at a distance of 400 mm on the left and right.