Aircraft radome opening and closing device

Abstract

The utility model relates to an airplane radar cover opening and closing device belongs to airplane accessory technical field, include: drive mechanism, quick detach assembly, movable assembly and limiting component, the fixed part of drive mechanism is fixed in the fuselage, quick detach assembly is fixed on the drive part of drive mechanism through the shaft coupling and is detachably connected with the screw rod on it, the threaded hole is equipped with on movable assembly and is screwed on the screw rod, the radar cover is fixed on movable assembly, limiting component includes first limit ring and second limit ring, and the first limit ring and second limit ring are fixed on the screw rod with the both ends of the movable assembly activity direction corresponding activity direction. The utility model first utilizes the drive part of drive mechanism to drive the screw rod to rotate with the airplane flight direction as the axis, and then the threaded hole of movable assembly is screwed on the screw rod, can limit the movable range of movable assembly, the opening and closing angle of radar cover is specified, prevents the excessive rotation radar cover and injures radar cover hinged piece.

Description

Technical Field

[0001] This utility model relates to the field of aircraft parts technology, and in particular to an aircraft radome opening and closing device. Background Technology

[0002] Aircraft radar systems are typically installed inside a radome at the front of the aircraft fuselage. The radome usually employs a folding design, hinged to an opening at the front of the fuselage. During ground maintenance of the aircraft radar system, it is necessary to open and close the system exposed inside the radome. However, the large size and weight of the aircraft radar system accessories make manual operation impossible; auxiliary tools are required for opening and closing. Furthermore, if the opening angle exceeds the specified value, it can easily damage the hinge.

[0003] To address the aforementioned technical issues, some research institutions have developed aircraft radome opening and closing devices. For example, patent number 201420134857.8, entitled "An Aircraft Radome Opening and Closing Device," describes a utility model patent where a hydraulic mechanism drives the radome's opening and closing. However, in practical use, ① the hydraulic system has strong power but lacks a force-limiting mechanism, easily leading to damage to the aircraft's nose-folding mechanism; ② the hydraulic system's telescopic drive lacks a limiting structure, still failing to prevent hinge damage; ③ the hydraulic system is prone to sealing failures, which can easily cause the aircraft radome's nose-folding mechanism to tumble rapidly, resulting in personnel injury and damage to accessories.

[0004] Therefore, how to design an aircraft radar opening and closing device with limited driving power, restricted driving position, and low malfunction rate is a problem that urgently needs to be solved by those skilled in the art. Utility Model Content

[0005] This invention provides an aircraft radome opening and closing device, which solves the technical problems of existing aircraft radome opening and closing devices having excessive driving power, uncontrollable opening and closing angles, and easy sealing failures.

[0006] The technical solution of this utility model to solve the above-mentioned technical problems is as follows: an aircraft radome opening and closing device, wherein the aircraft includes a fuselage and a radome, and the front end of the fuselage in the flight direction is provided with an opening; the radome is hinged at the opening; comprising: a drive mechanism, a quick-release assembly, a movable assembly, and a limiting assembly.

[0007] The fixed part of the drive mechanism is fixed inside the fuselage, and its drive part rotates about the flight direction of the fuselage as an axis. The quick-release assembly is fixed to the drive part of the drive mechanism via a coupling, and a lead screw is detachably connected to it, so that the lead screw is driven to rotate about the flight direction of the fuselage as the drive part of the drive mechanism rotates. The movable assembly has a threaded hole and is threadedly connected to the lead screw. The radome is fixed to the movable assembly and moves its position with the rotation of the lead screw, opening or closing the opening. The limiting assembly includes a first limiting ring and a second limiting ring, which are sleeved on the lead screw at both ends corresponding to the movement direction of the movable assembly to limit the range of movement of the movable assembly and regulate the opening and closing angle of the radome.

[0008] The beneficial effects of this utility model are: improving the structure of the traditional aircraft radome opening and closing device, firstly using the drive part of the drive mechanism to drive the lead screw to rotate around the aircraft's flight direction as the axis, and then threading the threaded hole of the movable component onto the lead screw. Since the first and second limiting rings are fixed on the lead screw at both ends corresponding to the movable component's movement direction, the range of motion of the movable component can be limited, the opening and closing angle of the radome can be standardized, and excessive rotation of the radome can prevent damage to the radome hinge.

[0009] Based on the above technical solution, the present invention can be further improved as follows.

[0010] Furthermore, the drive mechanism includes a fixed base and a manual / automatic motor. The fixed base is the fixed part of the drive mechanism and is fixed inside the body. The manual / automatic motor is fixed on the fixed base and its output shaft is the drive part of the drive mechanism. The quick-release assembly is fixed on the output shaft of the manual / automatic motor through a coupling.

[0011] The further beneficial effect of adopting the above is that by using a manual-automatic integrated motor to drive the lead screw to rotate, the radome can be manually opened after the aircraft loses power, improving the convenience of maintenance.

[0012] Furthermore, the manual / automatic motor includes a housing, a drive motor, a driven gear, a drive gear, and a crank handle. The housing is fixed to the mounting base and has a connecting hole and a through hole on its wall. The drive motor is fixed inside the housing, and its output shaft is the output shaft of the manual / automatic motor, which rotates through the through hole. The driven gear is located inside the housing, and its central hole is fitted outside the output shaft of the drive motor. The drive gear is rotatably connected inside the housing and meshes with the driven gear. One end of the crank handle can extend into the housing through the connecting hole and can be detachably inserted into the central hole of the drive gear to manually drive the output shaft of the drive motor to rotate.

[0013] The further beneficial effect of the above is that by using one end of the crank handle to pass through the connection hole and extend into the housing and insert it into the center hole of the drive gear, since the center hole of the drive gear is fixed to the extended end of the crank handle, the output shaft of the drive motor can be driven to rotate while the crank handle is turned, thereby realizing the manual opening of the radar dome.

[0014] Furthermore, the driving mechanism also includes a force limiting component, which has a fixing hole and is sleeved on the driving part of the driving mechanism.

[0015] The further beneficial effect of adopting the above is that by using the fixing hole of the force limiting component to fix it on the driving part of the driving mechanism, the driving force of the driving part can be prevented from being too large and damaging the radome hinge.

[0016] Furthermore, the quick-release assembly includes a sleeve and a pin. The sleeve is fixed to the drive part of the drive mechanism by a coupling and has a through-pin hole on its sleeve wall. One end of the lead screw can be detachably inserted into the sleeve and has a fixing pin hole at its insertion end. The pin can pass through the through-pin hole and be fixed in the fixing pin hole.

[0017] The further beneficial effects of the above are: firstly, the sleeve is fixed to the drive unit of the drive mechanism through the coupling, and then one end of the lead screw is detachably inserted into the sleeve. Since the pin can pass through the pin hole of the sleeve and be fixed in the pin hole of the lead screw, it is convenient to disassemble and assemble the lead screw and the sleeve, which facilitates later maintenance.

[0018] Furthermore, the movable component includes a movable seat and a docking seat, with the threaded hole provided on the movable seat; the docking seat is fixed on the movable seat; and the radar dome is fixed on the docking seat. Attached Figure Description

[0019] Figure 1 This is a three-dimensional structural diagram of an aircraft radome opening and closing device according to the present invention;

[0020] Figure 2 This is a schematic diagram of the connection structure of the crank, driving gear and driven gear in an aircraft radome opening and closing device according to the present invention.

[0021] The attached diagram lists the components represented by each number as follows:

[0022] 1. Drive mechanism; 11. Fixed seat; 12. Chassis; 13. Driven gear; 14. Drive gear; 15. Handle; 16. Force limiting component; 2. Quick release assembly; 21. Sleeve; 22. Pin; 3. Movable assembly; 31. Movable seat; 32. Connecting seat; 4. Limiting assembly; 41. First limiting ring; 42. Second limiting ring; 5. Coupling; 6. Lead screw. Detailed Implementation

[0023] The principles and features of this utility model are described below with reference to the accompanying drawings. The examples given are only for explaining this utility model and are not intended to limit the scope of this utility model.

[0024] like Figure 1 As shown, an aircraft radome opening and closing device is disclosed. The aircraft includes a fuselage and a radome, with an opening at the front end of the fuselage in the flight direction. The radome is hinged to the opening. The device includes: a drive mechanism 1, a quick-release assembly 2, a movable assembly 3, and a limiting assembly 4.

[0025] The fixed part of the drive mechanism 1 is fixed inside the fuselage, and its drive part rotates about the flight direction of the fuselage as an axis; the quick-release assembly 2 is fixed to the drive part of the drive mechanism 1 through the coupling 5, and a lead screw 6 is detachably connected to it, so as to drive the lead screw 6 to rotate about the flight direction of the fuselage as the drive part of the drive mechanism 1 rotates; the movable assembly 3 is provided with a threaded hole and is threadedly connected to the lead screw 6; the radome is fixed on the movable assembly 3, so as to move its position with the rotation of the lead screw 6, opening or closing the opening; the limiting assembly 4 includes a first limiting ring 41 and a second limiting ring 42, the first limiting ring 41 and the second limiting ring 42 are sleeved on the lead screw 6 at the two ends corresponding to the movement direction of the movable assembly 3, so as to limit the movement range of the movable assembly 3 and regulate the opening and closing angle of the radome.

[0026] like Figure 1 As shown, in some specific embodiments, the drive mechanism 1 may include a fixed base 11 and a manual / automatic motor. The fixed base 11 is the fixed part of the drive mechanism 1 and is fixed inside the body. The manual / automatic motor is fixed on the fixed base 11 and its output shaft is the drive part of the drive mechanism 1. The quick-release assembly 2 is fixed on the output shaft of the manual / automatic motor through a coupling 5.

[0027] like Figure 1 and Figure 2 As shown, in some specific embodiments, the manual / automatic motor may include a housing 12, a drive motor, a driven gear 13, a drive gear 14, and a crank handle 15. The housing 12 is fixed on the mounting base 11 and its walls are provided with a connecting hole and a through hole. The drive motor is fixed inside the housing 12 and its output shaft is the output shaft of the manual / automatic motor. The output shaft of the drive motor rotates through the through hole. The driven gear 13 is located inside the housing 12 and its central hole is fitted outside the output shaft of the drive motor. The drive gear 14 is rotatably connected inside the housing 12 and meshes with the driven gear 13. One end of the crank handle 15 can pass through the connecting hole and extend into the housing 12 and can be detachably inserted into the central hole of the drive gear 14 to manually drive the output shaft of the drive motor to rotate.

[0028] like Figure 1 As shown, in some specific embodiments, the drive mechanism 1 may further include a force limiting component 16, which has a fixing hole and is sleeved on the drive part of the drive mechanism 1.

[0029] like Figure 1 As shown, in some specific embodiments, the quick-release assembly 2 includes a sleeve 21 and a pin 22. The sleeve 21 is fixed to the drive part of the drive mechanism 1 by a coupling 5 and has a through pin hole on its sleeve wall. One end of the lead screw 6 can be detachably inserted into the sleeve 21 and its insertion end has a fixing pin hole. The pin 22 can pass through the through pin hole and be fixed in the fixing pin hole.

[0030] like Figure 1 As shown, in some specific embodiments, the movable component 3 may include a movable seat 31 and a docking seat 32, with a threaded hole provided on the movable seat 31; the docking seat 32 is fixed on the movable seat 31; and the radome is fixed on the docking seat 32.

[0031] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. An aircraft radome opening and closing device, the aircraft comprising a fuselage and a radome, a front end of the fuselage in a flight direction being provided with an opening hole; The radar dome is hinged at the opening; characterized in that it includes: ​ A drive mechanism (1) is provided, wherein the fixed part of the drive mechanism (1) is fixed inside the fuselage and its drive part rotates about the flight direction of the fuselage as an axis. Quick-release assembly (2), which is fixed to the drive part of the drive mechanism (1) by a coupling (5) and has a lead screw (6) detachably connected thereto, so as to drive the lead screw (6) to rotate about the flight direction of the fuselage as the drive part of the drive mechanism (1) rotates. The movable component (3) has a threaded hole and is threadedly connected to the lead screw (6); the radar cover is fixed to the movable component (3) so as to move its position with the rotation of the lead screw (6) to open or close the opening. The limiting component (4) includes a first limiting ring (41) and a second limiting ring (42). The first limiting ring (41) and the second limiting ring (42) are fixed on the lead screw (6) at both ends corresponding to the movement direction of the movable component (3) to limit the movement range of the movable component (3) and regulate the opening and closing angle of the radar dome.

2. An aircraft radome opening and closing device according to claim 1, characterised in that, The drive mechanism (1) includes a fixed base (11) and a manual / automatic motor. The fixed base (11) is the fixed part of the drive mechanism (1) and is fixed inside the body. The manual / automatic motor is fixed on the fixed base (11) and its output shaft is the drive part of the drive mechanism (1). The quick-release assembly (2) is fixed on the output shaft of the manual / automatic motor through a coupling (5).

3. An aircraft radome opening and closing device according to claim 2, characterised in that, The manual / automatic motor includes a housing (12), a drive motor, a driven gear (13), a drive gear (14), and a crank handle (15). The housing (12) is fixed on the fixed base (11) and has a connecting hole and a through hole on its housing wall. The drive motor is fixed inside the housing (12) and its output shaft is the output shaft of the manual / automatic motor. The output shaft of the drive motor rotates through the through hole. The driven gear (13) is located inside the housing (12) and its center hole is fitted outside the output shaft of the drive motor. The drive gear (14) is rotatably connected inside the housing (12) and meshes with the driven gear (13). One end of the crank handle (15) can pass through the connecting hole and extend into the housing (12) and can be detachably inserted into the center hole of the drive gear (14) to manually drive the output shaft of the drive motor to rotate.

4. An aircraft radome opening and closing device according to claim 1, wherein The drive mechanism (1) further includes a force limiting component (16), which has a fixing hole and is sleeved on the drive part of the drive mechanism (1).

5. An aircraft radome opening and closing device according to claim 1, wherein The quick-release assembly (2) includes a sleeve (21) and a pin (22). The sleeve (21) is fixed to the drive part of the drive mechanism (1) by a coupling (5) and has a through-pin hole on its sleeve wall. One end of the lead screw (6) can be detachably inserted into the sleeve (21) and its insertion end has a fixing pin hole. The pin (22) can pass through the through-pin hole and be fixed in the fixing pin hole.

6. The aircraft radome opening and closing device according to claim 1, characterized in that, The movable component (3) includes a movable seat (31) and a docking seat (32), the threaded hole is provided on the movable seat (31); the docking seat (32) is fixed on the movable seat (31); the radar dome is fixed on the docking seat (32).

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