CN104309799A - Aircraft cabin door lock mechanism - Google Patents
Aircraft cabin door lock mechanism Download PDFInfo
- Publication number
- CN104309799A CN104309799A CN201410557167.8A CN201410557167A CN104309799A CN 104309799 A CN104309799 A CN 104309799A CN 201410557167 A CN201410557167 A CN 201410557167A CN 104309799 A CN104309799 A CN 104309799A
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- Prior art keywords
- pressurized strut
- latch hook
- piston rod
- hook
- end cap
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- Fluid-Damping Devices (AREA)
Abstract
The invention provides an aircraft cabin door lock mechanism. The aircraft cabin door lock mechanism comprises a first end cover, an acting cylinder, a second end cover, a piston rod, a lock hook and a spring. According to the aircraft cabin door lock mechanism, the lock hook is hinged on the acting cylinder; one end of the lock hook is connected with the piston rod in the acting cylinder and the other end of the lock hook is hung on a cabin door lock ring; when the acting cylinder inflates to move a piston so that the lock hook can be driven to move and a cabin door is unlocked; and when gas in the acting cylinder is exhausted, the lock hook is driven by the piston to move so that the cabin door is locked. By adopting the structure, a locking principle of a traditional lock structure is simplified and the volume of the lock structure is reduced; and the aircraft cabin door lock mechanism is suitable for a small-size aircraft with high requirements on a small-layout space.
Description
Technical field
The invention belongs to small aircraft mechanism design technical field, particularly, relate to a kind of aircraft door latch mechanism.
Background technology
Reusable small aircraft is a kind of reusable Miniature Vehicle applicator platform with long-term flight, on a large scale orbit maneuver ability in-orbit.Reusable small aircraft relies on carrier rocket vertical launch to enter the orbit, adopt the offline mode of unpowered horizontal landing, executable space shuttle working, long-term resident and autonomous maneuver warfare in-orbit, supports to hit over the ground with service, sky in-orbit, Spatial powers combining military mission and the civilian task of space transportation such as quick roomage response.
For reusable small aircraft, need to be designed with Landing Gear System when returning landing, comprise undercarriage door jack and landing gear structure product, first by undercarriage door jack hatch door opened and could realize gear down function.Hatch door uplock and landing gear uplock are the critical function parts of loading door retractable mechanism and wheel-retracting gear, aircraft is in transmitting, in orbit stage, cabin door structure and landing gear structure are locked in retracted position to ensure the normal flight of aircraft by cabin door lock, when aircraft lands returns, open undercarriage door uplock and landing gear uplock by undercarriage door and gear down.
Small aircraft, because space is nervous, has higher requirement to the Miniaturization Design of Landing Gear System.Traditional uplock mechanism, realize the locking to uplock latched position by a mediation member, add the volume of latch mechanism, the latch mechanism developing a kind of miniaturization has very important construction value.
Summary of the invention
Technology of the present invention is dealt with problems and is: for the deficiencies in the prior art, provides a kind of principle simple aircraft door latch mechanism, to reduce the transmission component of common uplock mechanism.
For solving the problems of the technologies described above, the technical solution used in the present invention comprises:
A kind of aircraft door latch mechanism, comprise the first end cap, pressurized strut, the second end cap, piston rod, latch hook, spring, wherein, pressurized strut is installed on aircraft fuselage structures, pressurized strut has hollow cavity, and the first open end had as inlet end and the second open end; First end cap is threadedly connected to the first open end of pressurized strut, and first end covers the gas inlet-outlet having and be communicated with the hollow cavity of pressurized strut, and gas inlet-outlet is connected with outside supply air line; Second end cap is threadedly connected on the second open end of pressurized strut, and the second end cap has center hole; The first end of piston rod is arranged in the hollow cavity of pressurized strut, and its second end stretches out through the center hole on the second end cap from the second open end of pressurized strut; Spring housing fills on the piston rod, and under the state of nature of spring, one end of spring contacts with the first end of piston rod, and the other end of spring contacts with the second end cap; Latch hook is hinged in pressurized strut, further, the first end of latch hook is connected with the second end of piston rod, and the second end of latch hook is hook, for mounting with hatch door lock ring, and load-bearing direction on hook and the sense of motion of piston rod lay respectively at the both sides of the hinge-point of latch hook and pressurized strut.
Further, pressurized strut is provided with latch hook attaching parts, latch hook attaching parts is provided with the first connecting bore, latch hook is correspondingly provided with the second connecting bore, latch hook is by being arranged in the bolted splice of the first connecting bore and the second connecting bore; Second end of piston rod has transmission boss, and the first end of latch hook has U-shaped draw-in groove, and when installed, transmission boss is assemblied in U-shaped draw-in groove.
Further, the both sides of pressurized strut are respectively provided with two attachment lugs, and each attachment lug is provided with connecting bore, and pressurized strut is fixed to aircraft fuselage structures by the screw be arranged in each connecting bore.
The present invention's beneficial effect is compared with prior art:
The aircraft door latch mechanism proposed in the present invention, by latch hook is articulated with in pressurized strut, and one end of latch hook is connected with the piston rod in pressurized strut, the other end and the hatch door lock ring of latch hook mount, when making piston move to pressurized strut inflation, moveable lock hook action can be with, realize the unblock of hatch door; And after the gas in pressurized strut is discharged, latch hook action under the drive of piston again, realizes the locking of hatch door.This arrangement simplifies the locking principle of conventional lock designs, reduce the volume of lock construction, be applicable to the small aircraft high to little layout space requirements.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram according to latch mechanism of the present invention, and the latch mechanism in figure is in the lock state;
Fig. 2 a be the A-A of latch mechanism in Fig. 1 to cutaway view, Fig. 2 b is the decomposing schematic representation of Fig. 2 a;
Fig. 3 a and Fig. 3 b is respectively according to overall schematic during latch mechanism unlocking condition of the present invention and B-B to cutaway view;
Fig. 4 is according to principle of work schematic diagram during latch mechanism lock-out state of the present invention;
Fig. 5 is according to principle of work schematic diagram during latch mechanism released state of the present invention;
Fig. 6 is the schematic diagram according to pressurized strut of the present invention;
Fig. 7 is the schematic diagram according to the second end cap of the present invention;
Fig. 8 is the schematic diagram according to piston rod of the present invention;
Fig. 9 is the schematic diagram according to latch hook of the present invention.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, aircraft door latch mechanism according to the present invention is further described in detail.
First it should be noted that, aircraft door latch mechanism of the present invention is not limited to the locking of aircraft door, is also applicable to the locking of the similar structures such as alighting gear.
The present invention proposes a kind of undercarriage door and the landing gear uplock mechanism scheme that are applicable to small aircraft small space layout.This programme simplifies the locking principle of uplock, reduces the volume of lockout mechanism.Uplock structure in this programme in the locked state, a load moment is applied to latch hook by external bearer (namely by hatch door weight that hatch door lock ring transmits), apply an application force by the first end cap to pressurized strut piston rod simultaneously, thus latch hook is limited to latched position.When unblanking, cold gas system pressure promotes pressurized strut piston rod and applies a moment of unblanking to latch hook, and latch hook rotates to an angle, and realizes the unblock of latch mechanism to undercarriage door and alighting gear, undercarriage door and landing gear structure part is put down.Put down after putting in place, pressurized strut piston rod is returned to initial position by the built-in spring of pressurized strut, and band moveable lock hook gets back to latched position.
As shown in Fig. 1-Fig. 9, according to aircraft door latch mechanism of the present invention, comprise the first end cap, pressurized strut, the second end cap, piston rod, latch hook, spring.Wherein, pressurized strut 2 is installed on aircraft fuselage structures, and pressurized strut 2 has hollow cavity 201, and the first open end had as inlet end and the second open end; First end cap 1 is threadedly connected to the first open end of pressurized strut 2, and the first end cap 1 has the gas inlet-outlet 101 be communicated with the hollow cavity 201 of pressurized strut 2, and gas inlet-outlet 101 is connected with outside supply air line; Second end cap 3 is threadedly connected on the second open end of pressurized strut 2, and the second end cap 3 has center hole 301; The first end of piston rod 4 is arranged in the hollow cavity 201 of pressurized strut 2, and its second end stretches out through the center hole 301 on the second end cap 3 from the second open end of pressurized strut 2; Spring 6 is sleeved on piston rod 4, and under the state of nature of spring 6, one end of spring 6 contacts with the first end of piston rod 4, and the other end of spring 6 contacts with the second end cap 3; Latch hook 5 is hinged in pressurized strut 2, further, the first end of latch hook 5 is connected with the second end of piston rod 4, and the second end of latch hook 5 is hook, for mounting with hatch door lock ring, and load-bearing direction on hook and the sense of motion of piston rod lay respectively at the both sides of the hinge-point of latch hook and pressurized strut 2.
In the present invention, pressurized strut 2 is connected with airframe structure by fastener, and latch hook 5 coordinates with alighting gear or cabin door structure lock ring alighting gear or cabin door structure are limited to locking state.
Particularly, as shown in the figure, pressurized strut 2 is provided with latch hook attaching parts 202, latch hook attaching parts 202 is provided with the first connecting bore 203, latch hook 5 is correspondingly provided with the second connecting bore 501, latch hook 5 is by being arranged in the bolted splice of the first connecting bore 203 and the second connecting bore 501; Second end of piston rod 4 has transmission boss 401, and the first end of latch hook 5 has U-shaped draw-in groove, and when installed, transmission boss 401 is assemblied in U-shaped draw-in groove.The both sides of pressurized strut 2 are respectively provided with two attachment lugs 204, and each attachment lug 204 is provided with connecting bore, and pressurized strut 2 is fixed to aircraft fuselage structures by the screw be arranged in each connecting bore.
In the present invention, in order to realize the lock function of latch mechanism, needing to ensure that latch hook can hook into hatch door lock ring, for this reason, requiring that the sense of motion of load-bearing direction and the piston rod be applied on hook lays respectively at the both sides of the hinge-point of latch hook and pressurized strut.
Fig. 1 and Fig. 2 a, Fig. 2 b are the lock-out state schematic diagram of latch mechanism of the present invention.Alighting gear or hatch door load are passed to piston rod 4 by latch hook 5, piston rod 4 bears pressure load, pressure load is then passed to pressurized strut urceolus by piston rod 4, realizes the spacing of piston rod by pressurized strut urceolus, thus by alighting gear or hatch door load limit at lock-out state.
Fig. 3 a and Fig. 3 b is the unlocking condition schematic diagram of latch mechanism.When unblanking, high pressure gas enter pressurized strut 2 from the first end cap 1, promote piston rod 4, compress the spring 6 in pressurized strut, finally realize the unblock of latch mechanism when high pressure gas promote piston rod 4.When needs lock, first discharged by the high pressure gas in pressurized strut air cavity, pressurized strut piston rod 4 returns to lock-out state under the effect of built-in spring 6.
Fig. 4 is the fundamental diagram of latch mechanism at lock-out state, coercive mechanism 1 is the point of connection of latch hook and latch hook attaching parts, is articulated form, and coercive mechanism 2 is the point of connection of piston rod and latch hook, piston rod end designs a transmission boss, and transmission boss matches with the U-shaped draw-in groove on latch hook.In order to realize the locking of latch mechanism, in the present invention, the load-bearing of latch hook point is arranged on the left of coercive mechanism 1, latch hook load produces an anticlockwise moment relative to coercive mechanism 1, pressurized strut produces a limiting force to the right to piston rod, produce a clws moment, lock is remained on lock-out state by two moment balances.Meanwhile, as shown in Figure 2 a and 2 b, in the locked state, in the raw, its two ends contact with the second end cap with the first end of piston rod spring 6 respectively; And the first end of piston rod abuts the first end cap.
Fig. 5 is the principle of work schematic diagram of latch mechanism at unlocking condition.When unblanking, piston rod moves down under the impetus of high pressure gas, and band moveable lock hook rotates until leave hatch door lock ring around coercive mechanism 1 clockwise direction, and realize unlocking, now, built-in spring 6 is in compressive state.
At this, it should be noted that, the content do not described in detail in this specification sheets, be that those skilled in the art can be realized by the description in this specification sheets and prior art, therefore, do not repeat.
The foregoing is only the preferred embodiments of the present invention, be not used for limiting the scope of the invention.For a person skilled in the art, under the prerequisite not paying creative work, can make some amendments and replacement to the present invention, all such modifications and replacement all should be encompassed within protection scope of the present invention.
Claims (3)
1. an aircraft door latch mechanism, it is characterized in that, comprise the first end cap (1), pressurized strut (2), the second end cap (3), piston rod (4), latch hook (5), spring (6), wherein
Pressurized strut (2) is installed on aircraft fuselage structures, and pressurized strut (2) has hollow cavity (201), and the first open end had as inlet end and the second open end;
First end cap (1) is threadedly connected to the first open end of pressurized strut (2), and the first end cap (1) has the gas inlet-outlet (101) be communicated with the hollow cavity of pressurized strut (2) (201), gas inlet-outlet (101) is connected with outside supply air line;
Second end cap (3) is threadedly connected on the second open end of pressurized strut (2), and the second end cap (3) has center hole (301);
The first end of piston rod (4) is arranged in the hollow cavity (201) of pressurized strut (2), and its second end stretches out through the center hole (301) on the second end cap (3) from the second open end of pressurized strut (2);
Spring (6) is sleeved on piston rod (4), and under the state of nature of spring (6), one end of spring (6) contacts with the first end of piston rod (4), and the other end of spring (6) contacts with the second end cap (3);
Latch hook (5) is hinged in pressurized strut (2), and, the first end of latch hook (5) is connected with the second end of piston rod (4), second end of latch hook (5) is hook, for mounting with hatch door lock ring, and load-bearing direction on hook and the sense of motion of piston rod lay respectively at the both sides of the hinge-point of latch hook and pressurized strut (2).
2. aircraft door latch mechanism according to claim 1, is characterized in that,
Pressurized strut (2) is provided with latch hook attaching parts (202), latch hook attaching parts (202) is provided with the first connecting bore (203), latch hook (5) is correspondingly provided with the second connecting bore (501), latch hook (5) is by being arranged in the bolted splice of the first connecting bore (203) and the second connecting bore (501);
Second end of piston rod (4) has transmission boss (401), the first end of latch hook (5) has U-shaped draw-in groove (502), and when installed, transmission boss (401) is assemblied in U-shaped draw-in groove.
3. aircraft door latch mechanism according to claim 1, it is characterized in that, the both sides of pressurized strut (2) are respectively provided with two attachment lugs (204), (204) are provided with connecting bore to each attachment lug, and pressurized strut (2) is fixed to aircraft fuselage structures by the screw be arranged in each connecting bore.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410557167.8A CN104309799A (en) | 2014-10-20 | 2014-10-20 | Aircraft cabin door lock mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410557167.8A CN104309799A (en) | 2014-10-20 | 2014-10-20 | Aircraft cabin door lock mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104309799A true CN104309799A (en) | 2015-01-28 |
Family
ID=52365163
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410557167.8A Pending CN104309799A (en) | 2014-10-20 | 2014-10-20 | Aircraft cabin door lock mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104309799A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112373671A (en) * | 2020-12-12 | 2021-02-19 | 江西洪都航空工业集团有限责任公司 | Semi-active cabin door upper lock |
| CN113859545A (en) * | 2021-10-18 | 2021-12-31 | 中航通飞华南飞机工业有限公司 | Fire-extinguishing type airplane water-feeding cabin door |
| CN115137592A (en) * | 2022-08-02 | 2022-10-04 | 罗佳 | Movable nuclear magnetic resonance examination shielding cabin |
| US11541992B2 (en) * | 2019-02-28 | 2023-01-03 | Airbus Operations Limited | Landing gear retraction |
| CN117262284A (en) * | 2023-11-20 | 2023-12-22 | 杭州牧星科技有限公司 | Fixed wing unmanned aerial vehicle |
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| CN201456419U (en) * | 2009-07-31 | 2010-05-12 | 郑州宇通重工有限公司 | Front door opening mechanism for garbage compression box |
| CN201849373U (en) * | 2010-10-29 | 2011-06-01 | 包头北奔重型汽车有限公司 | Locking mechanism for back door of self-dumping truck |
| CN202249393U (en) * | 2011-09-30 | 2012-05-30 | 梁炳饶 | Gas spring door closer with simple structure |
| CN202689726U (en) * | 2012-08-26 | 2013-01-23 | 刘育宗 | Spring pneumatic cargo car body door locking and unlocking control device |
| CN203172500U (en) * | 2013-04-18 | 2013-09-04 | 李国祥 | Automatic locking device for container door |
| CN104006021A (en) * | 2014-06-12 | 2014-08-27 | 苏州劳灵精密机械有限公司 | Hinged inner rod type single-acting cylinder |
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Patent Citations (6)
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| CN201456419U (en) * | 2009-07-31 | 2010-05-12 | 郑州宇通重工有限公司 | Front door opening mechanism for garbage compression box |
| CN201849373U (en) * | 2010-10-29 | 2011-06-01 | 包头北奔重型汽车有限公司 | Locking mechanism for back door of self-dumping truck |
| CN202249393U (en) * | 2011-09-30 | 2012-05-30 | 梁炳饶 | Gas spring door closer with simple structure |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11541992B2 (en) * | 2019-02-28 | 2023-01-03 | Airbus Operations Limited | Landing gear retraction |
| CN112373671A (en) * | 2020-12-12 | 2021-02-19 | 江西洪都航空工业集团有限责任公司 | Semi-active cabin door upper lock |
| CN112373671B (en) * | 2020-12-12 | 2022-07-22 | 江西洪都航空工业集团有限责任公司 | Semi-active cabin door up lock |
| CN113859545A (en) * | 2021-10-18 | 2021-12-31 | 中航通飞华南飞机工业有限公司 | Fire-extinguishing type airplane water-feeding cabin door |
| CN115137592A (en) * | 2022-08-02 | 2022-10-04 | 罗佳 | Movable nuclear magnetic resonance examination shielding cabin |
| CN117262284A (en) * | 2023-11-20 | 2023-12-22 | 杭州牧星科技有限公司 | Fixed wing unmanned aerial vehicle |
| CN117262284B (en) * | 2023-11-20 | 2024-02-23 | 杭州牧星科技有限公司 | Fixed wing unmanned aerial vehicle |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150128 |
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| RJ01 | Rejection of invention patent application after publication |