Aircraft model fuselage lip special-shaped device

Abstract

The utility model discloses a kind of aircraft model fuselage lip department special-shaped devices, comprising: fuselage framework, head fairing, lip component and sealing assembly;Head fairing is fixedly arranged in the nose portion of the fuselage framework;Lip component is detachably arranged in the middle part of the fuselage framework, and adjacent to the head fairing, the lip component includes mounting ring, lip plate, right angle block, the mounting ring is fixedly connected with the fuselage framework, right angle block is detachably arranged on the mounting ring, the side of the right angle block away from fuselage framework is fixedly provided with lip plate, and a plurality of lip plate is enclosed in the periphery of the fuselage framework to form lip portion;Sealing assembly is arranged between the lip component and the head fairing;Through the parallel arrangement of fuselage framework, head fairing, lip component and sealing assembly, the modularization scheme of theoretical aerodynamic shape precision, fast, fixed-point maintenance can be effectively realized.

Description

Technical Field

[0001] This utility model relates to the technical field of pneumatic devices for the lip of an aircraft model, and in particular to a non-standard device for the fuselage lip of an aircraft model. Background Technology

[0002] Currently, the air intake lips of high-performance aircraft models are mostly formed by traditional hand-machining or integral machining processes. These methods are difficult to accurately reproduce the complex theoretical aerodynamic surfaces and are prone to intake distortion under high-speed conditions, leading to unstable power output and abnormal vibration.

[0003] Meanwhile, the integrated structural design means that the entire lip must be replaced after local damage, resulting in high maintenance costs and long cycles, which cannot meet the needs of high-frequency testing.

[0004] Existing technologies lack a modular lip structure solution that can both guarantee the accuracy of the theoretical aerodynamic shape and enable rapid, fixed-point maintenance. Utility Model Content

[0005] The purpose of this utility model is to overcome the shortcomings of the prior art and provide a non-standard lip device for the fuselage of an aircraft model, a modular lip structure solution that can both ensure the accuracy of the theoretical aerodynamic shape and achieve rapid, fixed-point maintenance.

[0006] The objective of this utility model is achieved through the following technical solution: a shaped fuselage lip device for an aircraft model, comprising a fuselage frame, a head skin, a lip assembly, and a sealing assembly; the head skin is fixedly disposed at the nose of the fuselage frame; the lip assembly is detachably disposed in the middle of the fuselage frame and adjacent to the head skin, the lip assembly including a mounting ring, a lip plate, and a right-angle block, the mounting ring being fixedly connected to the fuselage frame, the right-angle block being detachably disposed on the mounting ring, the lip plate being fixedly disposed on the side of the right-angle block away from the fuselage frame, and a plurality of lip plates surrounding the outer periphery of the fuselage frame to form a lip; the sealing assembly is disposed between the lip assembly and the head skin.

[0007] By splitting the original lip plate into several parallel lip plates, modular splicing, testing, and replacement can be achieved. The theoretical aerodynamic shape can be achieved through the setting of sealing components. The parallel setting of the fuselage frame, head skin, lip components, and sealing components can effectively achieve a modular solution for accurate, fast, and fixed-point maintenance of the theoretical aerodynamic shape.

[0008] The present invention is further configured such that: the mounting ring is a rigid ring with an L-shaped cross-section, and the mounting ring has a plurality of dovetail grooves on the side near the head, and the bottom of the right-angle block has a dovetail portion that matches the dovetail grooves.

[0009] The dovetail groove design can counteract the circumferential and torsional forces on the right-angle block, thereby achieving better stability.

[0010] The present invention is further configured such that: a fixing hole is provided in the dovetail groove, the right-angle block includes a fixing part connected to the lip plate, a connecting part perpendicular to the fixing part and a dovetail part embedded in the dovetail groove, and the side of the connecting part away from the fixing part is integrally formed with the dovetail part.

[0011] The fixing hole inside the dovetail groove can resist the radial test force and prevent radial dislodgement.

[0012] The present invention is further configured such that: a locking cavity is provided in the connecting part and the dovetail part; the locking cavity has a cross structure and its sides and bottom are completely penetrated; side buttons that at least partially extend out of the locking cavity are provided on both sides of the locking cavity; a longitudinal locking block is provided at the bottom; a longitudinal spring is provided between the longitudinal locking block and the locking cavity; and a lateral spring is provided between the side buttons and the locking cavity.

[0013] The longitudinal locking block installed inside the locking cavity can achieve a matching effect with the fixing hole. The side button can make the longitudinal locking block rise quickly, and the longitudinal spring can make it rebound quickly to form a quick-release structure, thereby making it easier to replace a certain component.

[0014] The present invention is further configured such that: a plurality of stacked sealing sheets with tails covering the next head are provided in the gap between the lip plate and the adjacent lip plate.

[0015] When airflow blows from the outside towards the seam, the airflow pressure will press the flexible sheet more tightly against the surface of the adjacent module, thereby achieving dynamic self-sealing. When disassembling the module, simply lift the sealing sheet gently.

[0016] The present invention is further configured such that: a hollow sealing strip, at least partially embedded in the lip plate, is provided between the lip plate and the adjacent lip plate.

[0017] The internal pressure (static pressure) of the air intake is similar to the external atmospheric pressure, and is relatively low. The sealing strip relies on its own elasticity to make slight contact with adjacent modules, providing a basic seal. As airspeed increases and airflow enters the air intake, its static pressure increases significantly. This increased pressure is transmitted to the back of the hollow sealing strip through the air duct. The air pressure squeezes the hollow sealing strip from the inside, causing it to expand radially outward like an inflated balloon. The expanded sealing strip presses more tightly against the mating surface of the adjacent module. The sealing pressure automatically increases with the increase of flight speed (intake pressure), achieving a tightening effect. When it is necessary to disassemble the module, the intake pressure disappears, the sealing strip retracts into the groove, and the module can be easily slid out.

[0018] This utility model has the following beneficial effects: by splitting the original lip plate into several parallel lip plates, modular splicing, testing, and replacement effects can be achieved; the sealing component can achieve the effect of theoretical aerodynamic shape; and the parallel arrangement of the fuselage frame, head skin, lip component, and sealing component can effectively achieve a modular solution with high accuracy, speed, and fixed-point maintenance of theoretical aerodynamic shape. Attached Figure Description

[0019] Figure 1 This is a partial schematic diagram of an embodiment of the present utility model; Figure 2 This is a first view of the lip component in an embodiment of the present invention; Figure 3 This is a second view of the lip component in an embodiment of the present invention; Figure 4 This is a cross-sectional view of the right-angled block in an embodiment of this utility model; Figure 5 This is a schematic diagram of the installation of the second sealing sheet in an embodiment of this utility model; Figure 6 This is a perspective view of the mounting ring in an embodiment of this utility model.

[0020] In the picture: 1. Head skin; 2. Lip plate; 3. Right-angle block; 31. Fixing part; 32. Connecting part; 33. Dovetail part; 34. Locking receiving cavity; 35. Longitudinal spring; 36. Side button; 37. Longitudinal locking block; 38. Lateral spring; 4. Mounting ring; 41. Dovetail groove; 42. Fixing hole; 5. Fuselage frame; 6. Stacked sealing sheet. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can typically be arranged and designed in various different configurations.

[0022] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0023] It should be noted that, where there is no conflict, the embodiments and features in the embodiments of this utility model can be combined with each other.

[0024] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0025] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this utility model is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0026] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0027] The following is in conjunction with the appendix Figure 1-6 The present invention will be described in further detail below, but the scope of protection of the present invention is not limited to the following description.

[0028] like Figure 1 As shown, an irregularly shaped fuselage lip device for an aircraft model includes: a fuselage frame 5, a head skin 1, a lip assembly, and a sealing assembly.

[0029] like Figure 1As shown, the head skin 1 is fixedly installed at the head of the fuselage frame 5. The head skin 1 is existing technology and belongs to an integral design that cannot be separated.

[0030] The lip assembly is detachably mounted in the middle of the fuselage frame 5 and is adjacent to the head skin 1; The lip assembly includes a mounting ring 4, a lip plate 2, and a right-angle block 3. The mounting ring 4 is fixedly connected to the fuselage frame 5. The right-angle block 3 is detachably provided on the mounting ring 4. The lip plate 2 is fixedly provided on the side of the right-angle block 3 away from the fuselage frame 5. Several lip plates 2 surround the outer periphery of the fuselage frame 5 to form a lip. like Figure 6 As shown, the mounting ring 4 is a rigid ring with an L-shaped cross-section. Several dovetail grooves 41 are provided on the side of the mounting ring 4 near the head. The bottom of the right-angle block 3 is provided with a dovetail part 33 that matches the dovetail grooves 41. The dovetail grooves 41 can offset the circumferential force and torsional force on the right-angle block 3, thereby achieving a better stability effect.

[0031] like Figure 4 , 6 As shown, a fixing hole 42 is provided in the dovetail groove 41. The right-angle block 3 includes a fixing part 31 connected to the lip plate 2, a connecting part 32 perpendicular to the fixing part 31, and a dovetail part 33 embedded in the dovetail groove 41. The dovetail part 33 is integrally formed on the side of the connecting part 32 away from the fixing part 31. The fixing hole 42 provided in the dovetail groove 41 can resist the radial test force and prevent radial dislodgement.

[0032] like Figure 4 As shown, a locking cavity 34 is provided in the connecting part 32 and the dovetail part 33. The locking cavity 34 has a cross structure and its sides and bottom are completely through. Side buttons 36 that extend at least partially out of the locking cavity 34 are provided on both sides of the locking cavity 34, and a longitudinal locking block 37 is provided at the bottom. A longitudinal spring 35 is provided between the longitudinal locking block 37 and the locking cavity 34, and a lateral spring 38 is provided between the side buttons 36 and the locking cavity 34. The longitudinal locking block 37 provided in the locking cavity 34 can achieve the effect of cooperating with the fixing hole 42. The side buttons 36 can make the longitudinal locking block 37 rise quickly, and the longitudinal spring 35 can make it rebound quickly to form a quick-release structure, thereby replacing a certain component more quickly.

[0033] like Figure 4 As shown, the side button 36 is provided with a slope, and the longitudinal locking block 37 is also provided with a corresponding slope, thereby achieving the effect of squeezing and lifting the longitudinal locking block 37.

[0034] A sealing assembly is disposed between the lip assembly and the head skin 1; the sealing assembly is a laminated sealing sheet 6.

[0035] like Figure 5As shown, several stacked sealing sheets 6 with their tails covering the next head are provided in the gap between the lip plate 2 and the adjacent lip plate 2; when the airflow blows from the outside to the joint, the airflow pressure will press the flexible sheet more tightly against the surface of the adjacent module, thereby achieving dynamic self-sealing. When disassembling the module, you only need to gently lift the sealing sheet.

[0036] Preferably, the sealing component can also be a hollow sealing strip, with grooves formed on the sidewalls of the lip plate 2 and adjacent lip plates 2; a hollow sealing strip, at least partially embedded in the lip plate 2, is provided between the lip plate 2 and adjacent lip plates 2; the internal pressure (static pressure) of the air intake is similar to the external atmospheric pressure, and the pressure is relatively low. The sealing strip relies on its own elasticity to make slight contact with the adjacent module, providing a basic seal. As the airspeed increases and airflow enters the air intake, its static pressure will increase significantly. This increased pressure is transmitted to the back of the hollow sealing strip through the air guide hole, and the air pressure will squeeze the hollow sealing strip from the inside, causing it to expand radially outward like an inflated balloon. The expanded sealing strip will press more tightly against the mating surface of the adjacent module, and the sealing pressure will automatically increase with the increase of flight speed (intake pressure), achieving a tightening effect. When it is necessary to disassemble the module, the intake pressure disappears, the sealing strip retracts into the groove, and the module can be easily slid out.

[0037] Preferably, the hollow sealing strip can be a cylinder or a cross structure, and the lip plate 2 has a corresponding structural groove on its side.

[0038] By splitting the original lip plate 2 into several parallel lip plates 2, modular splicing, testing, and replacement effects can be achieved. Furthermore, the effect of theoretical aerodynamic shape can be achieved through the setting of sealing components. The parallel setting of fuselage frame 5, head skin 1, lip components, and sealing components can effectively achieve a modular solution with high theoretical aerodynamic shape accuracy, speed, and fixed-point maintenance.

[0039] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A non-standard lip device for an aircraft model fuselage, characterized in that, include: Fuselage frame (5); The head skin (1) is fixedly installed at the head part of the fuselage frame (5); The lip assembly is detachably disposed in the middle of the fuselage frame (5) and adjacent to the head skin (1). The lip assembly includes a mounting ring (4), a lip plate (2), and a right-angle block (3). The mounting ring (4) is fixedly connected to the fuselage frame (5). The right-angle block (3) is detachably disposed on the mounting ring (4). The lip plate (2) is fixedly disposed on the side of the right-angle block (3) away from the fuselage frame (5). A plurality of the lip plates (2) surround the outer periphery of the fuselage frame (5) to form a lip. A sealing assembly is disposed between the lip assembly and the head skin (1).

2. The irregular shape device for the fuselage lip of an aircraft model according to claim 1, characterized in that: The mounting ring (4) is a rigid ring with an L-shaped cross-section. The mounting ring (4) has several dovetail grooves (41) on the side near the head. The bottom of the right-angle block (3) has a dovetail part (33) that matches the dovetail grooves (41).

3. The irregular shape device for the fuselage lip of an aircraft model according to claim 2, characterized in that: The dovetail groove (41) is provided with a fixing hole (42). The right-angle block (3) includes a fixing part (31) connected to the lip plate (2), a connecting part (32) perpendicular to the fixing part (31), and a dovetail part (33) embedded in the dovetail groove (41). The dovetail part (33) is integrally formed on the side of the connecting part (32) away from the fixing part (31).

4. The irregular shape device for the fuselage lip of an aircraft model according to claim 3, characterized in that: The connecting part (32) and the dovetail part (33) are provided with locking receiving cavities (34). The locking receiving cavity (34) has a cross structure and its two sides and bottom are completely penetrated. The two sides of the locking receiving cavity (34) are provided with side buttons (36) that extend at least partially out of the locking receiving cavity (34), and the bottom is provided with a longitudinal locking block (37). A longitudinal spring (35) is provided between the longitudinal locking block (37) and the locking receiving cavity (34), and a lateral spring (38) is provided between the side button (36) and the locking receiving cavity (34).

5. The irregular shape device for the fuselage lip of an aircraft model according to any one of claims 1-4, characterized in that: A plurality of stacked sealing sheets (6) with their tails covering the next head are provided in the gap between the lip plate (2) and the adjacent lip plate (2).

6. The irregular shape device for the fuselage lip of an aircraft model according to any one of claims 1-4, characterized in that: A hollow sealing strip, at least partially embedded in the lip plate (2), is provided between the lip plate (2) and the adjacent lip plate (2).

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