An active panel rotation mechanism for a variable Mach number nozzle of a hypersonic wind tunnel

Abstract

The present invention discloses a movable panel rotation mechanism for a hypersonic wind tunnel variable Mach number nozzle, specifically relating to the technical field of hypersonic aircraft ground test equipment. A movable panel rotation mechanism for a hypersonic wind tunnel variable Mach number nozzle comprises a fixed housing connected to the nozzle, a groove formed on the fixed housing, a movable panel slidably and sealedly connected in the groove, a driver provided on one side of the movable panel, a rotating shaft connection structure provided on the other side of the movable panel, a rotating shaft mounting hole provided at the lower end of the rotating shaft connection structure, symmetrically arranged movable panel rotating shafts rotatably connected to the fixed housing, and each movable panel rotating shaft is arranged in a corresponding mounting hole. The technical solution of the present invention solves the problem of mutual interference between the sealing structure and the rotating shaft between the fixed structure and the movable panel of the hypersonic wind tunnel variable Mach number nozzle, avoids the influence of the rotating shaft on the sealing performance, and can obtain good sealing and motion characteristics.

Description

Technical Field

[0001] The present invention relates to the technical field of hypersonic aircraft ground test equipment, and in particular to a movable panel rotation mechanism for a hypersonic wind tunnel variable Mach number nozzle. Background Art

[0002] Hypersonic wind tunnels are key equipment for conducting ground tests of hypersonic aircraft. They can simulate the airflow environment during hypersonic flight and conduct experimental research on the aerodynamic forces, thermal structure, and internal flow and combustion characteristics of the aircraft's engines during flight. As a key component of a hypersonic wind tunnel, its function is to accelerate the airflow to the speed required for testing. Since aircraft undergo changes such as acceleration, deceleration, and climb during flight, in order to study the impact of these changes on the aircraft's flight state and its engine operating mode, hypersonic wind tunnels must be able to simulate variable airflow parameters. Therefore, the wind tunnel nozzle must be able to change the outlet airflow velocity by changing the internal structure and shape.

[0003] Since hypersonic vehicles typically fly at Mach numbers between 4 and 7, with total temperatures between 900K and 2100K and total pressures between 1MPa and 6.5MPa, wind tunnel nozzles must operate under high-temperature and high-pressure conditions. For variable-Mach-number nozzles, the Mach number and other state parameters of the nozzle outlet airflow must continuously change according to test requirements, requiring the nozzle profile structure to adapt to changes in nozzle outlet airflow parameters. Changes to the nozzle profile are typically achieved through rotation, with the profile structure and fixed components utilizing a dynamic sealing structure. To ensure that the nozzle's sealing structure does not affect the rotation of moving components, while also ensuring the effectiveness of the dynamic seal during movement under high-temperature and high-pressure conditions, and to avoid damage to the nozzle structure due to leakage of high-temperature and high-pressure gases, the design of the rotating structure between the nozzle's moving profile and stationary components is particularly important.

[0004] At present, the existing hypersonic wind tunnel variable Mach number nozzle profile rotation structure at home and abroad usually adopts a built-in rotating shaft structure. Due to the limitations of space, structure and high temperature and high pressure working conditions of the nozzle, the nozzle dynamic seal and the rotating structure often interfere with each other, which brings certain difficulties to the design and manufacture of the nozzle. Therefore, it is urgent to design a movable panel rotation mechanism for the hypersonic wind tunnel variable Mach number nozzle to solve the interference problem between the variable Mach number nozzle dynamic seal and the rotating shaft, avoid the mutual influence between the rotating shaft and the dynamic seal performance, and obtain good sealing and motion characteristics. Summary of the Invention

[0005] The present invention aims to provide a movable panel rotation mechanism for a hypersonic wind tunnel variable Mach number nozzle, which solves the problem that existing wind tunnel nozzles cannot achieve Mach number changes during wind tunnel tests.

[0006] In order to achieve the above-mentioned purpose, the technical solution of the present invention is as follows: A movable panel rotation mechanism of a hypersonic wind tunnel variable Mach number nozzle comprises a fixed box body connected to the nozzle, a groove is provided on the fixed box body, a movable panel is slidingly and sealingly connected in the groove, a driver is provided on one side of the movable panel, a rotating shaft connection structure is provided on the other side of the movable panel, a rotating shaft mounting hole is provided at the lower end of the rotating shaft connection structure, symmetrically arranged movable panel rotating shafts are rotatably connected to the fixed box body, and each of the movable panel rotating shafts is arranged in a corresponding mounting hole.

[0007] Preferably, a graphite packing dynamic sealing structure is adopted between the movable panel and the groove.

[0008] Through the above arrangement, dynamic sealing performance can be achieved under high temperature and high pressure conditions during the relative movement of the fixed phase lift and the movable panel.

[0009] Compared with the existing technology, this solution has the following beneficial effects:

[0010] This solution adopts an external rotating structure to avoid interference between the dynamic sealing structure and the rotating shaft, greatly reducing the cost of designing and manufacturing the test device, while achieving good dynamic sealing performance and motion characteristics. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 This is an axial side view of a movable panel rotation mechanism of a hypersonic wind tunnel variable Mach number nozzle according to the present invention;

[0012] Figure 2 This is a front view of a movable panel rotation mechanism of a hypersonic wind tunnel variable Mach number nozzle according to the present invention. DETAILED DESCRIPTION

[0013] The present invention will be further described in detail below through specific embodiments:

[0014] The reference numerals in the drawings of the specification include: a fixed box 1, a movable panel 2, a rotating shaft connection structure 3, a rotating shaft 4, a driver connection structure 5, and a graphite packing 6.

[0015] Example

[0016] As attached Figure 1 and attached Figure 2The figure shows a movable panel rotation mechanism for a variable Mach number hypersonic wind tunnel nozzle. The mechanism comprises a fixed housing 1 connected to the nozzle. One side of the fixed housing 1 has an air inlet connected to the nozzle, and the other side of the fixed housing 1 has an air outlet coplanar with the air inlet. A groove is formed at the top of the fixed housing 1, into which a movable panel 2 is slidingly and sealingly connected. A graphite packing 6 is provided between the movable panel 2 and the groove. This ensures a dynamic seal between the two, thereby maintaining the reliability of the system under high temperature conditions. The left side of the movable panel 2 is connected to a driver via a drive connection structure. The right side of the movable panel 2 is provided with a rotating shaft connection structure 3. The rotating shaft connection structure 3 comprises two "L"-shaped connecting rods and a fixed block connected between the two connecting rods. The lower end of the rotating shaft connection structure 3 is provided with a mounting hole for a rotating shaft 4. Each mounting hole for the rotating shaft 4 is rotatably connected to the side wall of the fixed housing 1.

[0017] During operation, the driver on the movable panel 2 applies force to the left side of the movable panel 2 to drive it up and down, causing the movable panel 2 to rotate around the rotating shaft 4. At this time, the position of the movable panel 2 and the lower surface of the fixed box 1 changes continuously, thereby realizing a continuous change in the Mach number of the airflow discharged from the nozzle.

[0018] The above are only embodiments of the present invention, and common knowledge such as the specific structure and / or characteristics of the scheme are not described in detail here. It should be pointed out that for those skilled in the art, without departing from the structure of the present invention, several variations and improvements can be made, which should also be regarded as the scope of protection of the present invention, and these will not affect the effect of the implementation of the present invention and the practicality of the patent. The scope of protection required by this application shall be based on the content of its claims, and the specific implementation methods and other records in the specification can be used to interpret the content of the claims.

Claims

1. A movable panel rotation mechanism for a hypersonic wind tunnel variable Mach number nozzle, characterized by: It includes a fixed box body connected to the nozzle, a groove is opened on the fixed box body, a movable panel is slidingly and sealedly connected in the groove, a driver is provided on one side of the movable panel, a rotating shaft connection structure is provided on the other side of the movable panel, a rotating shaft mounting hole is provided at the lower end of the rotating shaft connection structure, and symmetrically arranged movable panel rotating shafts are rotatably connected to the fixed box body, and each of the movable panel rotating shafts is set in a corresponding mounting hole.

2. The movable panel rotation mechanism for a hypersonic wind tunnel variable Mach number nozzle according to claim 1, characterized in that: A graphite packing dynamic sealing structure is adopted between the movable panel and the groove.

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