Anti-sink mechanism for blocked cabin door of an aircraft
By designing an anti-sinking mechanism that includes a latch groove, a latch, a pawl, and a spline shaft, the problem of unbalanced structural forces during the opening and closing of aircraft doors was solved, achieving simple operation and lightweight design.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
- Filing Date
- 2023-11-16
- Publication Date
- 2026-06-26
AI Technical Summary
Existing aircraft door blocking anti-sinking mechanisms have the problem of being either simple in structure but having a large load or complex in structure and heavy in weight.
Design an anti-sinking mechanism including a latch groove, a latch, a pawl, a splined shaft, a rocker arm, and a retaining spring. The pawl automatically locks the latch when the hatch is opened to prevent the latch shaft from rotating, and automatically releases the lock when the hatch is closed. The pawl's stop boss cooperates with the limit stop pin to achieve simple operation of the hatch.
It achieves the goal of preventing sinking when the hatch is open, has a large locking lever arm and good force distribution, is easy to operate when the hatch is closed, and has a simple overall structure and light weight.
Smart Images
Figure CN117432296B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of aircraft blocking door anti-sinking design, specifically relating to an aircraft blocking door anti-sinking mechanism. Background Technology
[0002] Aircraft blocking doors typically employ the following two technical solutions to prevent sinking:
[0003] 1) The design involves a torsion spring driving a support block to rotate and press against the latch shaft during the hatch opening process, when the hatch is raised to its highest position and about to move away from the door frame. This prevents the latch shaft from rotating in the opposite direction and thus prevents the hatch from sinking. This technical solution has a simple structure, but the support block directly presses against the latch shaft. In the locked state, the lever arm is small, the load on the support block is large, and the stress condition is not good.
[0004] 2) The design involves using a handle to drive a functional locking mechanism during the hatch opening process. When the hatch is raised to its highest position and is about to move away from the door frame, the latch shaft is locked to prevent it from rotating in the opposite direction, thus preventing the hatch from sinking. This technical solution has a complex structure and is relatively heavy.
[0005] This application is made in view of the aforementioned technical deficiencies.
[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention
[0007] The purpose of this application is to provide an aircraft blocking door anti-sinking mechanism to overcome or mitigate at least one of the known technical defects.
[0008] The technical solution of this application is:
[0009] An aircraft blocking door anti-sinking mechanism includes: a door, a door frame, a latch groove, a latch, a pawl, a splined shaft, a rocker arm, a retaining spring, and a limit stop pin;
[0010] The latch groove is fixed to the door frame, with one end being the sealed end and the other end being the open end;
[0011] The latch includes a latch roller, a latch crank, and a latch shaft. The latch roller is engaged in a latch groove. The latch shaft is mounted on the hatch and connected to the hatch handle via a linkage mechanism. The hatch handle can drive the latch shaft to rotate via the linkage mechanism.
[0012] The spline shaft runs through the side frame of the hatch. One end of the spline shaft on the inside of the side frame is connected to the rocker arm, and the other end of the spline shaft on the inside of the side frame is connected to the pawl via a spline joint.
[0013] The pawl sidewall has a stop boss and the end has a crimping arc surface;
[0014] The limit stop pin is connected to the outer side of the side frame of the hatch;
[0015] The spring is connected between the rocker arm and the hatch. Relying on the elastic force, through the rocker arm and the spline shaft, the stop boss on the side wall of the pawl abuts against the open end of the latch groove.
[0016] When the hatch is opened, it is lifted upward relative to the door frame, which drives the latch shaft to rotate, causing the latch roller to roll towards the open end in the latch groove. When the hatch is lifted to the highest position and is about to leave the door frame, the latch roller slides out from the open end of the latch groove, and the stop boss on the side wall of the pawl disengages from the open end of the latch groove. Under the action of the spring elastic force, it abuts against the limit stop pin, and the end pressing arc surface fits against the curved surface of the latch crank end to prevent the latch shaft from rotating.
[0017] When the hatch is closed, the latch roller slides into the open end of the latch groove, and the latch shaft is driven to rotate by the hatch handle. The latch roller rolls towards the sealing end in the latch groove. The curved surface at the end of the latch crank disengages from the pressing arc surface at the end of the pawl. The hatch sinks relative to the door frame, and the stop boss on the side wall of the pawl abuts against the open end of the latch groove. The latch roller slides to the sealing end of the latch groove.
[0018] According to at least one embodiment of this application, the above-described aircraft blocking door anti-sinking mechanism further includes a nut and a washer.
[0019] The spline axis has a shoulder at one end inside the side frame;
[0020] Nuts and washers are installed on the outer end of the spline shaft on the side frame, so that the shoulder on the spline shaft abuts against the side frame and the pawl is tightened.
[0021] According to at least one embodiment of this application, the above-described aircraft blocking door anti-sinking mechanism further includes a locking nut and a locking washer.
[0022] The limit stop pin is set through the side frame of the hatch;
[0023] Locking nuts and locking washers are installed at the end of the limit stop pin on the inside of the side frame for locking.
[0024] According to at least one embodiment of this application, in the above-described aircraft blocking door anti-sinking mechanism, the retaining spring is connected to the rocker arm and the door via a hook and an ear hole.
[0025] This application has at least the following beneficial technical effects:
[0026] A blocking mechanism for preventing aircraft door from sinking is provided. During the door opening process, when the door is raised to its highest position and about to move away from the door frame, a pawl automatically locks the latch to prevent the latch shaft from rotating, thus preventing the door from sinking. The pawl is locked at the end of the latch crank, resulting in a large lever arm and good force distribution. Furthermore, when the door is closing and about to enter the door frame position, the pawl can be automatically released by pressing the open end of the latch groove, allowing the door to sink and close. The mechanism is simple to operate, has a simple overall structure, and is lightweight. Attached Figure Description
[0027] Figure 1 This is a schematic diagram of the structure of the aircraft blocking door anti-sinking mechanism provided in the embodiments of this application;
[0028] Figure 2 This is an assembly diagram of the aircraft blocking door anti-sinking mechanism provided in the embodiments of this application;
[0029] Figure 3 This is a schematic diagram of the latch structure provided in an embodiment of this application;
[0030] Figure 4 This is a schematic diagram showing the cabin door in a closed state under the action of the aircraft blocking cabin door anti-sinking mechanism provided in the embodiments of this application;
[0031] Figure 5 This is a schematic diagram showing the aircraft door being lifted to its highest position and about to move away from the door frame during the opening process, under the action of the aircraft blocking door anti-sinking mechanism provided in this application embodiment;
[0032] Figure 6 This is a schematic diagram of the aircraft door being in the open state under the action of the aircraft blocking door anti-sinking mechanism provided in the embodiments of this application;
[0033] in:
[0034] 1-Hatch door; 2-Door frame; 3-Latch groove; 4-Latch; 5-Nut; 6-Washer; 7-Pawl; 8-Splined shaft; 9-Rocker arm; 10-Retaining spring; 11-Locking nut; 12-Locking washer; 13-Limit stop pin;
[0035] 41-Latch roller; 42-Latch crank; 43-Latch shaft.
[0036] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation
[0037] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.
[0038] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.
[0039] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.
[0040] The following is in conjunction with the appendix Figures 1 to 5 This application will be described in further detail.
[0041] An aircraft door blocking anti-sinking mechanism includes: a door 1, a door frame 2, a latch groove 3, a latch 4, a nut 5, a washer 6, a pawl 7, a splined shaft 8, a rocker arm 9, a retaining spring 10, a locking nut 11, a locking washer 12, and a limit pin 13. Figure 1, Figure 2 As shown.
[0042] The latch groove 3 is fixed on the door frame 2, with one end being the sealed end and the other end being the open end.
[0043] The latch 4 includes a latch roller 41, a latch crank 42, and a latch shaft 43, as shown below. Figure 3 As shown, the latch roller 41 is engaged in the latch groove 3; the latch shaft 43 is mounted on the hatch 1 and connected to the hatch handle through a linkage mechanism, and the hatch handle can drive the latch shaft 43 to rotate through the linkage mechanism.
[0044] The spline shaft 8 is set through the side frame of the hatch 1. The end of the spline shaft 8 on the inner side of the side frame has a shoulder, which is connected to the rocker arm 9. The end of the spline shaft 8 on the inner side of the side frame is connected to the pawl 7 through a spline pair, and a nut 5 and a washer 6 are installed at this end so that the shoulder on the spline shaft 8 is against the side frame to prevent the spline shaft 8 from moving axially and to tighten the pawl 7.
[0045] The pawl 7 has a stop boss on its side wall and a crimping arc surface at its end.
[0046] The limit pin 13 is set through the side frame of the hatch 1, and a locking nut 11 and a locking washer 12 are installed on the end inside the side frame for locking.
[0047] The spring 10 is connected between the rocker arm 9 and the hatch 1, specifically through a hook and an ear hole. Relying on the elastic force, the stop boss on the side wall of the pawl 7 abuts against the open end of the latch groove 3 via the rocker arm 9 and the spline shaft 8.
[0048] When hatch 1 is opened, it rises relative to door frame 2, causing latch shaft 43 to rotate. This causes latch roller 41 to roll towards the open end in latch groove 3. When hatch 1 is raised to its highest position and is about to move away from door frame 2, latch roller 41 slides out of the open end of latch groove 3. The stop boss on the side wall of pawl 7 disengages from the open end of latch groove 3 and, under the elastic force of retaining spring 10, abuts against limit stop pin 13. The end pressing arc surface fits against the curved surface of latch crank 42. Figure 5 As shown, to prevent the latch shaft 43 from rotating, this prevents the hatch 1 from sinking during the opening process. The hatch 1 is in the open state as shown. Figure 6 As shown.
[0049] When hatch 1 is closed, latch roller 41 slides into the open end of latch groove 3, driving latch shaft 43 to rotate via hatch handle. Latch roller 41 rolls towards the sealing end in latch groove 3, the curved surface at the end of latch crank 42 disengages from the pressing arc surface at the end of pawl 7, hatch 1 sinks relative to door frame 2, the stop boss on the side wall of pawl 7 abuts against the open end of latch groove 3, latch roller 41 slides to the sealing end of latch groove 3, hatch 1 is closed, and hatch 1 is in the closed state as follows: Figure 4 As shown.
[0050] Regarding the aircraft blocking door anti-sinking mechanism disclosed in the above embodiments, those skilled in the art will understand that its design involves the pawl 7 automatically locking the latch 4 when the door 1 is opened and raised to its highest position and about to move away from the door frame, preventing the latch shaft 43 from rotating and thus preventing the door from sinking. The pawl 7 is locked at the end of the latch crank 42, with a large lever arm and good force distribution. When the door 1 is closed and about to enter the door frame 2, the pawl 7 can be automatically unlocked by the open end of the latch groove 3, allowing the door 1 to sink and close. The operation is simple, the overall structure is simple, and it has a small weight.
[0051] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.
Claims
1. An aircraft door blocking anti-sinking mechanism, characterized in that, include: Hatch door (1), door frame (2), latch groove (3), latch (4), pawl (7), spline shaft (8), rocker arm (9), retaining spring (10), limit stop pin (13); The latch groove (3) is fixed on the door frame (2), with one end being the sealed end and the other end being the open end; The latch (4) includes a latch roller (41), a latch crank (42), and a latch shaft (43), wherein the latch roller (41) is engaged in the latch groove (3); the latch shaft (43) is mounted on the hatch (1) and connected to the hatch handle through a linkage mechanism, and the hatch handle can drive the latch shaft (43) to rotate through the linkage mechanism; The spline shaft (8) is set through the side frame of the hatch (1). The end of the spline shaft (8) on the inside side frame is connected to the rocker arm (9). The end of the spline shaft (8) on the inside side frame is connected to the pawl (7) through a spline pair. The pawl (7) has a stop boss on its side wall and a pressing arc surface at its end; The limiting pin (13) is connected to the outside of the side frame of the hatch (1); The spring (10) is connected between the rocker arm (9) and the hatch (1). Relying on the elastic force, through the rocker arm (9) and the spline shaft (8), the stop boss on the side wall of the pawl (7) abuts against the open end of the latch groove (3). When the hatch (1) is opened, it is lifted upward relative to the door frame (2), which drives the latch shaft (43) to rotate, causing the latch roller (41) to roll towards the open end in the latch groove (3). When the hatch (1) is lifted to the highest position and is about to move away from the door frame (2), the latch roller (41) slides out from the open end of the latch groove (3), and the stop boss on the side wall of the pawl (7) disengages from the open end of the latch groove (3). Under the action of the elastic force of the retaining spring (10), it abuts against the limit stop pin (13), and the end pressing arc surface fits against the end curved surface of the latch crank (42) to prevent the latch shaft (43) from rotating. When the hatch (1) is closed, the latch roller (41) slides into the open end of the latch groove (3), and the latch shaft (43) is driven to rotate by the hatch handle. The latch roller (41) rolls towards the blocking end in the latch groove (3). The curved surface at the end of the latch crank (42) disengages from the arc surface pressed by the end of the pawl (7). The hatch (1) sinks relative to the door frame (2). The stop boss on the side wall of the pawl (7) abuts against the open end of the latch groove (3). The latch roller (41) slides to the blocking end of the latch groove (3).
2. The aircraft blocking door anti-sinking mechanism according to claim 1, characterized in that, It also includes nuts (5) and washers (6); The spline shaft (8) has a shoulder at one end inside the side frame; Nut (5) and washer (6) are installed on the outside end of the spline shaft (8) on the side frame, so that the shoulder on the spline shaft (8) is against the side frame and the pawl (7) is tightened.
3. The aircraft blocking door anti-sinking mechanism according to claim 1, characterized in that, It also includes a lock nut (11) and a lock washer (12); The limit stop pin (13) is set through the side frame of the hatch (1); The locking nut (11) and locking washer (12) are installed at the end of the limit stop pin (13) on the inside of the side frame for locking.
4. The aircraft blocking door anti-sinking mechanism according to claim 1, characterized in that, The spring (10) is connected to the rocker arm (9) and the hatch (1) by means of a hook and an ear hole.