Air cannon support structure suitable for aircraft engine whole-machine ice swallowing and bird swallowing test

Abstract

The air cannon sabot structure of the present invention, suitable for use in aircraft engine whole-unit ice and bird swallowing tests, comprises a bushing and a sabot base. A slot for mounting a flying bird or hailstone is defined in the central region of the bushing. Multiple arresting cables are disposed on one side of the bushing, adjacent to the slot, and sequentially pass through the bushing and sabot base. Each arresting cable has an extension at each end that passes through the sabot base, and is secured by a fixing rod between adjacent extensions. This prevents other structures from being ejected during bird launch.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation engine swallowing test, and in particular relates to an air cannonball support structure suitable for aviation engine whole machine ice and bird swallowing test. Background Art

[0002] The sabot is a key consumable component in conducting high-pressure air cannon-based aircraft engine ice and bird swallowing tests. Its primary function is to maintain the structural integrity of the projectile, hailstone, or bird during the release, acceleration, and separation phases before it leaves the high-pressure air cannon barrel, ensuring the projectile exits with a complete shape and a velocity that meets the test requirements. The sabot consists of three parts: a barrel, a base, and an inner liner. The barrel and base are cylindrical and generally made of lightweight metal. They cooperate with the inner wall of the barrel to ensure the linearity of the flight trajectory and withstand release and separation loads. The inner liner, typically made of foam plastic, directly contacts the projectile, providing shock absorption and securing the projectile. The inner liner is secured to the base with adhesive and forms a tight fit with the inner wall of the barrel, with a clearance of less than 0.5 mm. After assembly, this gap is filled with adhesive. During use, the projectile is placed in a cylindrical groove on the inner liner surface.

[0003] Since the whole-machine test of aircraft engines requires high launch pressure and launch speed, and the large difference in temperature and humidity in the sabot operating environment leads to poor bonding effect of the adhesive, during the hail or bird swallowing test, it is easy for the lining to be loosely fixed and fall off before separating from the projectile, causing the lining to wrap around the projectile and be ejected, or the lining to hit the projectile, etc., which seriously affects the safe operation of the tested aircraft engine, the structural integrity of the projectile when it leaves the barrel and is ejected, and the accuracy of the incident path and impact velocity. Summary of the Invention

[0004] In view of this, the present invention provides an air cannonball support structure suitable for ice and bird swallowing tests of aircraft engines, which solves the technical problem of the existing structure in which the liner is ejected during hail or bird swallowing tests.

[0005] An air cannon cartridge support structure for an aircraft engine ice and bird swallowing test is provided, which is characterized in that it includes a bushing and a cartridge support base, a groove for mounting hail or flying birds is provided in a central area of ​​the bushing, and a plurality of arresting cables are provided on a side surface of the bushing and adjacent to the groove, which pass through the bushing and the cartridge support base in sequence, each of the arresting cables has an extended section at both ends, which passes through the cartridge support base, and is fastened by a fixing rod between two adjacent extended sections.

[0006] Beneficial effects of the present invention:

[0007] The newly added arresting cable at the bottom of the sabot achieves both physical and chemical fixation of the liner, optimizing the ventilation environment for the adhesive inside the sabot and enhancing the adhesive's bonding effectiveness. By using a liner material with greater plasticity and lower density, the liner's inertial force under high-speed and heavy-load conditions was reduced. During tests of the complete aircraft engine swallowing ice and birds, effective separation of the projectile from the sabot was achieved. No excess material, such as the liner or liner fragments, followed the projectile out of the high-pressure air cannon. The projectile's structure remained intact, and its flight path was stable. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0009] Figure 1 It is a structural schematic diagram of the present invention;

[0010] Figure 2 This is a schematic diagram of the connection between the extension section and the fixed rod teeth of the present invention;

[0011] Figure 3 is a schematic diagram of the assembled present invention;

[0012] Figure 4 A schematic diagram of a retaining ring provided in the present invention;

[0013] in:

[0014] 1. Barrel; 2. Bushing; 3. Sabot base; 4. Fixing rod; 5. Arresting cable; 6. Gun barrel; 7. Retaining ring. DETAILED DESCRIPTION

[0015] The embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0016] The following describes the embodiments of the present invention through specific examples. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0017] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present invention, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement an apparatus and / or practice a method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this apparatus and / or practice this method.

[0018] like Figure 1 The air cannon cartridge support structure shown for the aircraft engine whole machine ice and bird swallowing test includes a bushing 2 and a cartridge support base 3. A groove 21 for installing hail or flying birds is provided in the central area of ​​the bushing 2. A plurality of arresting cables 5 are provided on one side surface of the bushing 2 and adjacent to the groove. The arresting cables 5 are preferably arranged in a concave structure, and the number of arresting cables 5 is generally 4. An extension section is left at both ends of each arrester, which passes through the extension section of the cartridge support base 3 and is fastened by a fixing rod 4 between two adjacent extension sections. Preferably, it also includes a cylinder 1 with an open structure at both ends, wherein: the cartridge support base 3 is installed at one end of the cylinder 1, for example, fixed by threaded connection, welding, or nesting. As shown Figure 2 As shown, each extended section extending from the bullet support base 3 is provided with teeth of a preset length, and both ends of the fixing rod 4 are connected to the adjacent extended sections by tooth engagement, or both ends of the fixing rod 4 are welded to the adjacent extended sections.

[0019] Four newly added circumferentially distributed mounting / ventilation ports at the bottom of the sabot, combined with arresting cables, achieve both physical and chemical fixation of the liner, optimizing the ventilation environment for the adhesive within the sabot and enhancing the adhesive's bonding effectiveness. By using a liner material with greater plasticity and lower density, the liner's inertial force under high-speed and heavy-load conditions was reduced. During tests of the complete aircraft engine swallowing ice and birds, effective separation of the projectile from the sabot was achieved. No excess material, such as the liner or liner fragments, followed the projectile out of the high-pressure air cannon, maintaining the projectile's structural integrity and maintaining a stable flight path.

[0020] Furthermore, in order to improve the fixation of the bushing 2, the circumferential surface of the bushing 2 and the side surface facing the support base 3 are connected to the barrel 1 and the support base 3 respectively by bonding.

[0021] Secondly, an air cannon is provided, such as Figure 4As shown, it includes a gun barrel 6, which launches part or all of the above-mentioned air cannon shell support structure, and a retaining ring 7 is provided at the exit position of the gun barrel 6 to prevent the air cannon shell support structure from detaching from the gun barrel 6.

[0022] After the air cannon shell support structure is assembled Figure 3 As shown, it is installed in the gun barrel 6. When the air cannon shell support structure is launched, the retaining ring 7 can prevent the barrel 1 from breaking away from the gun barrel 6, and only the hail or flying bird launching position is tested.

[0023] In actual use, the barrel 1 and the sabot base 4 are machined together using a transition fit tolerance. When installing barrel 1 onto the sabot base 4, ensure that it is level and check that there is no significant circumferential difference in the gap at the bottom of the inner wall. After installation, apply adhesive around the perimeter. Apply pearl foam adhesive to the inner surfaces of barrel 1 and sabot base 4. Place the EPE liner 2 horizontally. Once fully seated, rotate it to ensure uniform contact between the cylindrical surface and the adhesive. Let the sabot stand in a dry and ventilated area for 48 hours. After the adhesive has dried, pull the EPE liner 2 to check the adhesion. Tear of the liner is considered the standard for bond strength. The number of arresting cables 3 is selected based on the test speed and launch pressure. Generally, for pressures not exceeding 0.6 MPa and speeds not exceeding 100 m / s, two arresting cables 3 are used for securing. The arresting cables 3 are symmetrically threaded through the mounting holes 5 on the sabot base 4. Tighten the arresting cables 3 to press the EPE liner 2 against the sabot base 4, completely securing the EPE liner 2. The projectile can then be inserted for testing.

[0024] The above are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. An air cannon comprising a cannon barrel, characterized in that: The air cannon also includes an air cannon buttress structure, which includes a bushing and a buttress base. A groove for mounting a bird or hail is provided in a central region of the bushing. A plurality of arresting cables are provided on a side surface of the bushing and adjacent to the groove, and pass through the bushing and the buttress base in sequence. Each arresting cable has an extension section at both ends, which passes through the buttress base, and is fastened between two adjacent extension sections by a fixing rod. Each extension section extending from the buttress base is provided with a tooth of a preset length, and both ends of the fixing rod are connected to the adjacent extension section by tooth meshing. A retaining ring is provided at the gun barrel outlet position to prevent the air projectile support structure from detaching from the gun barrel.

2. The air cannon according to claim 1, characterized in that: It also includes a cylinder with openings at both ends, wherein the cartridge base is installed at one end of the cylinder.

3. The air cannon according to claim 2, characterized in that: The circumferential surface of the bushing and the side surface facing the support base are respectively connected to the barrel and the support base by bonding.

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