Inward opening type opening mechanism of airplane cabin door
By designing an open opening mechanism for the drone door and using hinges to connect and adjust the connecting rod, the problem of opening the cabin door during flight affects the aircraft's driving, and the full utilization of the cabin space is achieved.
Patent Information
- Application Number
- CN202421434756.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-21
- Publication Date
- 2025-05-02
- Estimated Expiration
- 2034-06-21
AI Technical Summary
The existing drone door design affects the aircraft's driving when the door is opened during flight and cannot make full use of the interior space of the cabin.
An open opening mechanism for the aircraft cabin door is designed, including the hatch door, connecting support, adjustment link, actuator and connector. Through the use of hinged connection and adjustment link, the internal opening opening of the hatch door is realized.
It reduces the impact of opening the hatch door during the aircraft flight on the aircraft's driving, and makes full use of the interior space of the cabin.
Smart Images
Figure CN222823075U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an inward opening mechanism for an aircraft cabin door. Background Art
[0002] The UAV cabin door is an important and special moving part in the UAV fuselage. It has a complex design and strict functional requirements. Not only that, it must also meet the requirements of stiffness, strength, fatigue, airtightness, reliability, etc.
[0003] However, in the prior art, since the cabin door design is restricted by many factors, especially for aircraft with high size requirements, the cabin door is significantly affected by the arrangement of various aircraft components; for example, when the aircraft is transferred through a standard container, the tail part of the rear fuselage of the aircraft cannot be raised; the traditional clamshell-type outward-opening cabin door cannot meet the problem that the opening of the cabin door during the flight seriously affects the aircraft driving, and at the same time, in order to meet the requirements of cargo transportation in and out, the space inside the cabin must be fully utilized; therefore, under this background, an aircraft cabin door opening mechanism is designed to avoid and reduce the impact of opening the cabin door during the flight on the aircraft driving, with a simple and lightweight structure, and can fully utilize the space inside the cabin. Utility Model Content
[0004] The technical problem to be solved by the utility model is to provide an inward opening mechanism for an aircraft cabin door, which can reduce the impact of opening the cabin door during the flight of the aircraft on the aircraft driving and make full use of the internal space of the cabin.
[0005] In order to solve the above technical problems, the technical solution of the utility model is:
[0006] An inward opening mechanism for an aircraft cabin door comprises a cabin door, a connecting support, an adjusting connecting rod, an actuator and a connecting body, wherein the cabin door comprises a first cabin door and a second cabin door, and the first cabin door and the second cabin door are connected by a hinge;
[0007] The connecting support includes a connecting rod fixing support, a fuselage support, a first door support, a second door support, an actuator support and a door frame support, wherein the fuselage support is arranged at one side of the first door and is fixed to the first door through the first door support; the second door support is arranged at one side of the second door, one end of the adjusting connecting rod is arranged on the second door support, and the connecting rod fixing support is arranged at the other end of the adjusting connecting rod;
[0008] One end of the actuating cylinder is arranged on the second cabin door, and the connecting body is arranged on the other end of the actuating cylinder.
[0009] Preferably, an adapter is provided between the connecting rod fixing support and the adjusting connecting rod.
[0010] Preferably, the actuator cylinder is connected to the second cabin door via an actuator cylinder support, and the actuator cylinder is connected to the connecting body via a door frame bracket.
[0011] Preferably, the first door can be deflected around the central axis of the fuselage support.
[0012] Preferably, the second hatch can be deflected around the central axis of the hinge.
[0013] Preferably, the deflection direction of the adjusting link relative to the adapter is perpendicular to the deflection direction of the first hatch.
[0014] By adopting the above technical solution, since the second door support is arranged on one side of the second door, one end of the adjusting connecting rod is arranged on the second door support, and the connecting rod fixing support is arranged on the other end of the adjusting connecting rod; one end of the actuator cylinder is arranged on the second door, so that the impact of opening the door during the flight of the aircraft on the aircraft driving is reduced and the internal space of the cabin is fully utilized. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 It is a schematic diagram of the structure of the utility model;
[0016] Figure 2 This is a schematic diagram of the operating structure of the utility model;
[0017] Figure 3 It is a side view of the utility model.
[0018] In the figure, 1-hatch door, 2-connecting support, 3-adjusting connecting rod, 4-actuator, 5-connector, 6-hinge, 7-adapter, 101-first hatch door, 102-second hatch door, 201-connecting rod fixing support, 202-fuselage support, 203-first hatch door support, 204-second hatch door support, 205-actuator support, 206-door frame support. DETAILED DESCRIPTION
[0019] The specific implementation methods of the present invention are further described below in conjunction with the accompanying drawings. It should be noted that the description of these implementation methods is used to help understand the present invention, but does not constitute a limitation of the present invention. In addition, the technical features involved in each implementation method of the present invention described below can be combined with each other as long as they do not conflict with each other.
[0020] like Figure 1-3 As shown, an inward opening mechanism of an aircraft cabin door comprises a cabin door, a connecting support, an adjusting connecting rod, an actuator and a connecting body, wherein the cabin door comprises a first cabin door and a second cabin door, and the first cabin door and the second cabin door are connected by a hinge;
[0021] The connecting support includes a connecting rod fixing support, a fuselage support, a first hatch door support, a second hatch door support, an actuator support and a door frame support. The fuselage support is arranged on one side of the first hatch door and is fixed to the first hatch door through the first hatch door support; the second hatch door support is arranged on one side of the second hatch door, one end of the adjusting connecting rod is arranged on the second hatch door support, and the connecting rod fixing support is arranged on the other end of the adjusting connecting rod;
[0022] One end of the actuator is arranged on the second cabin door, and the connecting body is arranged on the other end of the actuator.
[0023] In addition, an adapter is provided between the connecting rod fixing support and the adjusting connecting rod.
[0024] Furthermore, the actuator cylinder is connected to the second cabin door via an actuator cylinder support, and the actuator cylinder is connected to the connecting body via a door frame bracket.
[0025] Additionally, the first door may be pivotable about a central axis of the fuselage support.
[0026] Furthermore, the second hatch can be deflected around the central axis of the hinge.
[0027] In addition, the deflection direction of the adjusting link relative to the adapter is perpendicular to the deflection direction of the first door.
[0028] Working principle:
[0029] One end of the actuator is set on the fuselage through a connecting piece, and the other end of the actuator is connected to the second door through an actuator support. The first door and the second door are connected by a hinge, and the first door is connected to the fuselage through a fixed support. When the actuator contracts, the actuator will pull the second door to move upward. While the second door moves upward, the first door will deflect upward around the fuselage support. Since one end of the adjusting link is fixed to the fuselage through the fuselage support, and the other end of the adjusting link is connected to the second door through the second door support, the deflection of the first door is transmitted in reverse to the second door, so that the second door deflects downward relative to the first door, thereby realizing the inward folding and opening of the door.
[0030] The embodiments of the present invention are described in detail above with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. For those skilled in the art, various changes, modifications, substitutions and variations of these embodiments are made without departing from the principles and spirit of the present invention, and still fall within the scope of protection of the present invention.
Claims
1. An inward opening mechanism for an aircraft cabin door, characterized in that: It comprises a door, a connecting support, an adjusting connecting rod, an actuator and a connecting body, wherein the door comprises a first door and a second door, and the first door and the second door are connected by a hinge; The connecting support includes a connecting rod fixing support, a fuselage support, a first door support, a second door support, an actuator support and a door frame support, wherein the fuselage support is arranged at one side of the first door and is fixed to the first door through the first door support; the second door support is arranged at one side of the second door, one end of the adjusting connecting rod is arranged on the second door support, and the connecting rod fixing support is arranged at the other end of the adjusting connecting rod; One end of the actuating cylinder is arranged on the second cabin door, and the connecting body is arranged on the other end of the actuating cylinder.
2. The inward opening mechanism for an aircraft cabin door according to claim 1, characterized in that: An adapter is provided between the connecting rod fixing support and the adjusting connecting rod.
3. The inward opening mechanism for an aircraft cabin door according to claim 1, characterized in that: The actuating cylinder is connected to the second cabin door via an actuating cylinder support, and the actuating cylinder is connected to the connecting body via a door frame bracket.
4. The aircraft cabin door inward opening mechanism according to claim 1, characterized in that: The first door can be deflected around the central axis of the fuselage support.
5. The inward opening mechanism for an aircraft cabin door according to claim 1, characterized in that: The second hatch can be deflected about the central axis of the hinge.
6. The aircraft cabin door inward opening mechanism according to claim 2, characterized in that: The deflection direction of the adjusting connecting rod relative to the adapter is perpendicular to the deflection direction of the first cabin door.