Aircraft hydraulic test device

Abstract

The utility model discloses an airplane hydraulic test device, which belongs to the technical field of airplane equipment detection and comprises a connector, a sealing cover plate, a bolt, a blocking cover and a product end face sealing gasket. A center round hole is formed in the center of each sealing cover plate, a threaded through hole communicated with the center round hole is formed in the side wall of each sealing cover plate and used for being connected with the corresponding connector 1, the two sealing cover plates are oppositely clamped on the two sides of the fuel oil electric plug board switch and clamped and fixed through bolts, and a product end face sealing gasket is clamped between each sealing cover plate and the fuel oil electric plug board switch to achieve sealing. Blocking covers are hermetically mounted on the outer sides of the central circular holes of the two sealing cover plates; the connector 1 is used for refueling and pressure maintaining to check whether oil leaks or not. The device is simple and practical in structure, can improve the hydraulic test efficiency after the airplane fuel electric plugboard switch is disassembled, and reduces the scrap probability.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft equipment testing technology and relates to an aircraft hydraulic testing device. Background Technology

[0002] A certain type of aircraft has several electric fuel filler switches. To ensure a leak-proof seal under certain pressures (0.02MPa and 0.98MPa), end-face sealing must be performed on both sides of the electric fuel filler switch, and the pressure must be maintained for three minutes to check for leaks. Current technology employs a multi-person collaborative approach: one person holds the electric fuel filler switch port in hand while another person uses a vise to perform hydraulic fuel injection. This method lacks dedicated testing equipment and is inherently unstable (personnel cannot leave the site during operation) and unsafe. It easily leads to wasted hydraulic fluid, damage to interface accessories, and consequently affects the overall repair of the fuel system components and the overall maintenance cycle of the thermal protection system. Utility Model Content

[0003] Based on the characteristics and usage requirements of the electric fuel switch for a certain aircraft, this utility model provides an aircraft hydraulic testing device. It employs a combination of end-face and clamp-type designs. After sealing both end faces, fuel can be applied to one side while observation is possible on the other. If no leakage is observed after applying fuel to one side, the product is deemed to have passed the test. This utility model features a simple structure, safe use, and convenient operation, making it the optimal choice for hydraulic testing of the electric fuel switch for this type of product. Furthermore, due to the commonality of the circular hole portion in related electric fuel switches, this utility model can be extended to hydraulic testing of the same model in automobiles, ships, and other similar applications by modifying the end hole size.

[0004] The present invention adopts the following technical solution:

[0005] An aircraft hydraulic testing device, comprising a connector 1, a rubber gasket 2, a sealing cover 3, bolts 4, a baffle 5, and a product end face sealing gasket 6.

[0006] The sealing cover plate 3 is a square plate with a certain thickness. It has a central circular hole with internal threads. The inner diameter of the central circular hole is the same as the outer diameter of the left and right cavities of the fuel electric switch. A threaded through hole communicating with the central circular hole is made on one side wall of the sealing cover plate 3 for connecting the connector 1. A rubber gasket 2 is installed at the joint between the connector 1 and the sealing cover plate 3 to achieve a seal. There are through holes at the four corners of the sealing cover plate 3. There are two sealing cover plates 3 with the same structure. The two are clamped on both sides of the fuel electric switch. After clamping, four bolts 4 are passed through the through holes at the four corners of the two sealing cover plates 3 and fixed with hexagonal thin nuts and flat washers.

[0007] The cover 5 has an external thread on its outer circumference and a hexagonal rotating head on one side surface. There are two covers 5, which are installed from the outside on the central holes of the two sealing cover plates 3. An O-ring is installed at the joint between the cover 5 and the sealing cover plate 3 to achieve a seal.

[0008] The product end face sealing gasket 6 is clamped between the sealing cover plate 3 and the fuel electric plug switch to achieve end face sealing of the fuel electric plug switch.

[0009] The beneficial effects of this utility model are: the structure of this utility model is simple and practical, which can improve the hydraulic test efficiency after the disassembly of the aircraft fuel electric switch, reduce the scrapping probability, and thus shorten the overall combat readiness cycle. Attached Figure Description

[0010] Figure 1 This is an overall structural diagram of the present invention, wherein (a) is a front view and (b) is a side view.

[0011] Figure 2 The diagram shows the joint structure, where (a) is the front view and (b) is the side view.

[0012] Figure 3 This is a cross-sectional view of the rubber pad.

[0013] Figure 4 This is a schematic diagram of the sealing cover structure, where (a) is the front view and (b) is the side view.

[0014] Figure 5 The diagram shows the bolt structure, where (a) is the front view and (b) is the side view.

[0015] Figure 6 This is a schematic diagram of the cover structure, where (a) is the front view and (b) is the side view.

[0016] The components include: 1. Connector; 2. Rubber gasket; 3. Sealing cover; 4. Bolt; 5. Cover; 6. Product end face sealing gasket. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this utility model clearer, the specific embodiments of this utility model will be described in detail below.

[0018] An aircraft hydraulic testing device includes a connector 1, a rubber gasket 2, a sealing cover 3, bolts 4, a retaining cover 5, and a product end face sealing gasket 6, as shown below. Figure 1 .

[0019] The sealing cover 3 is a square plate with a certain thickness, such as... Figure 4It has a central circular hole with an internal thread, the inner diameter of which is the same as the outer diameter of the left and right cavities of the fuel electric switch. A threaded through hole communicating with the central circular hole is formed on one side wall of the sealing cover 3, for connecting the connector 1 (e.g., Figure 2 A rubber gasket 2 is installed at the junction of connector 1 and sealing cover plate 3 (e.g., Figure 3 To achieve a seal, the sealing cover 3 has four corner holes. Two sealing cover plates 3 with identical structures are clamped onto both sides of the fuel-electric switch. After clamping, they are secured using four bolts 4 (such as...). Figure 5 It passes through the four corner holes of the two sealing cover plates and is fixed by using hexagonal thin nuts and flat washers.

[0020] like Figure 6 The cover 5 has an external thread on its outer circumference and a hexagonal rotating head on one side surface. There are two covers 5, which are installed from the outside on the central holes of the two sealing cover plates 3. An O-ring is installed at the junction of the cover 5 and the sealing cover plate 3 to achieve a seal.

[0021] The product end face sealing gasket 6 is clamped between the sealing cover plate 3 and the fuel electric plug switch to achieve end face sealing of the fuel electric plug switch.

[0022] In use: Clamp the two sealing covers 3 opposite each other on both sides of the fuel-electric switch. Install the product end-face sealing gasket 6 between the sealing covers 3 and the fuel-electric switch. This can be done on one side or both sides simultaneously. After clamping, use four bolts 4 to pass through the holes at the four corners of the two sealing covers 3, and use hexagonal thin nuts and flat washers to achieve double-sided clamping, forming a sealed structure between the fuel-electric switch and the hydraulic testing device. Apply oil to the end face of the fuel-electric switch through connector 1. If only one side has the product end-face sealing gasket 6 clamped, apply oil to the connector 1 on the unclamped side. After testing one side, move the product end-face sealing gasket 6 to the other side for another test. If both sides have the product end-face sealing gasket 6 clamped, apply oil simultaneously from both connectors 1. After oiling, maintain pressures at 0.02MPa and 0.98MPa respectively, performing two tests at each pressure, maintaining each test for three minutes. Observe for oil leakage during the test. For single-side oiling, observe for oil leakage by opening the plug 6 on the other side.

[0023] In summary, the above are merely preferred embodiments of this utility model and are not intended to limit the scope of protection of this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the scope of protection of this utility model.

Claims

1. An aircraft hydraulic test device, characterized in that The hydraulic testing device includes a connector (1), a sealing cover (3), bolts (4), a baffle (5), and a product end face sealing gasket (6); The sealing cover (3) is a square plate with a certain thickness. It has a central circular hole with an internal thread. Its inner diameter is the same as the outer diameter of the left and right cavities of the fuel electric switch. A threaded through hole communicating with the central circular hole is made on one side wall of the sealing cover (3) for connecting the connector (1). The sealing cover (3) has through holes at the four corners. There are two sealing covers (3) with the same structure. They are clamped on both sides of the fuel electric switch. Four bolts (4) pass through the through holes at the four corners of the two sealing covers (3) and are fixed. The cover (5) has external threads on its outer circumference, and there are two of them, which are installed from the outside on the central holes of the two sealing cover plates (3); The product end face sealing gasket (6) is sandwiched between the sealing cover plate (3) and the fuel electric plug switch to achieve end face sealing of the fuel electric plug switch.

2. An aircraft hydraulic test apparatus as claimed in claim 1, wherein, A rubber gasket (2) is installed at the junction of the connector (1) and the sealing cover plate (3) to achieve a seal.

3. The aircraft hydraulic testing device according to claim 1, characterized in that, An O-ring is installed at the junction of the cover (5) and the sealing cover (3) to achieve a seal.

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