CN214690153U - Linkage protection mechanism for emergency control undercarriage - Google Patents
Linkage protection mechanism for emergency control undercarriage Download PDFInfo
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- CN214690153U CN214690153U CN202120987279.2U CN202120987279U CN214690153U CN 214690153 U CN214690153 U CN 214690153U CN 202120987279 U CN202120987279 U CN 202120987279U CN 214690153 U CN214690153 U CN 214690153U
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- base
- control switch
- landing gear
- mounting plate
- guide hole
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Abstract
The utility model discloses an emergent undercarriage linkage protection mechanism that manipulates comprises parts such as fixed mounting board, undercarriage control switch, unable adjustment base, light guide panel, spacing separation blade and hatch door control switch. The beneficial effects of the utility model reside in that: by utilizing the mechanical design, the interlocking between the control switches of the opening and closing doors of the landing gear is realized, namely, the landing gear of the airplane can be put down only after the landing gear door is opened, so as to avoid danger.
Description
Technical Field
The utility model relates to an aircraft undercarriage controlling means, especially, emergent control undercarriage linkage protection mechanism.
Background
The landing gear of the airplane mainly has the functions of bearing the gravity of the airplane during parking, sliding and takeoff (landing), consuming and absorbing the impact energy of the airplane during landing, braking during sliding and operating the airplane (turning) during sliding and sliding. Therefore, the effective retraction of the landing gear of the aircraft, and in particular the lowering of the landing gear, is directly related to the safety of the aircraft. Emergency operation of the landing gear is of critical importance since the landing gear system must ensure landing gear extension if the landing gear retraction system fails. The emergency control landing gear is an independent system, and after the emergency control landing gear is started, the emergency control landing gear can be put down under the action of gravity and pneumatic power, so that the safe landing of an airplane is ensured. At present, cabin door control switch operation space is small in the existing linkage protection mechanism, the whole appearance is ugly, the flip operation is inconvenient, the operation is possibly influenced, and potential safety hazards exist.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the problem in the prior art and providing a novel linkage protection mechanism of an emergency control undercarriage.
In order to realize the purpose, the technical scheme of the utility model is as follows: an emergency control undercarriage linkage protection mechanism comprises,
the mounting plate comprises a fixed mounting plate and a fixed mounting plate, wherein the fixed mounting plate is provided with a mounting plate left area and a mounting plate right area, the mounting plate left area is provided with a left area guide hole extending along the left-right direction, and the mounting plate right area is provided with a right area guide hole extending along the front-back direction;
an undercarriage control switch for controlling the landing gear of an aircraft to be lowered, the undercarriage control switch being disposed below the mounting plate right area, the undercarriage control switch being secured to the mounting plate right area, the undercarriage control switch having a toggle handle passing upwardly through the right area guide hole, the toggle handle having at least a non-lowered work position at a rear end and a lowered work position at a front end;
the fixed base is provided with a base bottom wall, a base front wall and a base rear wall, the base bottom wall is arranged on the top surface of the left area of the installation plate, the base bottom wall is fixed on the left area of the installation plate, and the base bottom wall is provided with a base guide hole extending along the left-right direction;
the light guide panel is arranged on the top surface of the front wall of the base and the top surface of the rear wall of the base, the light guide panel, the front wall of the base, the bottom wall of the base and the rear wall of the base define a guide channel extending along the left-right direction together, and a panel guide hole extending along the left-right direction is formed in the light guide panel;
the limiting baffle is arranged in the guide channel, a baffle fixing hole is formed in the limiting baffle, and the panel guide hole, the baffle fixing hole, the bottom wall guide hole and the left area guide hole are in the same vertical plane;
the cabin door control switch is used for controlling the opening and closing of the landing gear cabin door, the cabin door control switch is arranged below the left area of the installation plate, the cabin door control switch is fixed in the left area of the installation plate, the cabin door control switch is provided with a pulling vertical shaft, and the pulling vertical shaft upwards penetrates through the left area guide hole, the base guide hole, the baffle fixing hole and the panel guide hole, so that the pulling vertical shaft can be pulled leftwards and rightwards, and synchronously acts with the limiting baffle, and the pulling vertical shaft at least has an opening working position at the left end and a closing working position at the right end;
in the initial state, the wrenching handle is arranged at the undeployed working position, the wrenching vertical shaft is arranged at the closed working position, and at the moment, the limiting blocking piece blocks the front of the wrenching handle to limit the wrenching handle to be wrenched forwards;
when the wrenching vertical shaft is wrenched from the closing working position to the opening working position, the wrenching vertical shaft drives the limiting blocking piece to move leftwards to release the blocking of the wrenching handle, so that the wrenching handle can be wrenched forwards to put down the aircraft landing gear.
As a preferred solution for the emergency operation landing gear linkage protection mechanism, the hatch control switch is provided with a protective cover for preventing the pulling vertical shaft from being operated by mistake.
As a preferred scheme of the emergency control undercarriage linkage protection mechanism, the limiting blocking piece is provided with a blocking piece through hole extending in the front-back direction, a spring and a steel ball are arranged in the blocking piece through hole, the spring is arranged at the inner end, the steel ball is arranged at the outer end, and the steel ball is abutted against the front wall of the base or the rear wall of the base.
As the preferred scheme of the emergency control undercarriage linkage protection mechanism, the light guide panel is made of aircraft glass. The light guide panel is hollow.
As a preferred scheme of the emergency control undercarriage linkage protection mechanism, the cabin door control switch is fixed in the left area of the mounting plate through a U-shaped mounting bracket.
Compared with the prior art, the beneficial effects of the utility model reside in at least: by utilizing the mechanical design, the interlocking between the control switches of the opening and closing doors of the landing gear is realized, namely, the landing gear of the airplane can be put down only after the landing gear door is opened, so as to avoid danger.
Drawings
Fig. 1 is an external view of an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail below with reference to the accompanying drawings by way of specific embodiments. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. Furthermore, the technical features mentioned in the embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.
Referring to fig. 1 and 2, an emergency gear linkage protection mechanism is shown.
The emergency control undercarriage linkage protection mechanism comprises a fixed mounting plate 1, an undercarriage control switch 2, a fixed base 3, a light guide panel 4, a limiting baffle 5, a cabin door control switch 6 and the like.
The fixed mounting plate 1 is a flat plate. The fixed mounting plate 1 is provided with a mounting plate left area and a mounting plate right area. The mounting plate left area is formed with a left area guide hole extending in the left-right direction. The right area of the mounting plate is formed with a right area guide hole extending in the front-rear direction.
The landing gear control switch 2 is used for controlling the landing gear of the airplane to be put down. The landing gear control switch 2 is a pull-type hydraulic switch. The landing gear control switch 2 is arranged below the right region of the mounting plate. The landing gear control switch 2 is fixed to the mounting plate right region. The landing gear control switch 2 has a toggle handle 61. The pulling handle 61 passes upward through the right-area guide hole. The pulling handle 61 has at least an undeployed working position at the rear end and a deployed working position at the front end. In the initial state, the toggle handle 61 is in the undeployed operating position, at which time the aircraft landing gear is not being lowered. When the toggle handle 61 is toggled from the undeployed work position to the lowered work position, the aircraft landing gear is lowered.
The stationary base 3 has a base bottom wall 31, a base front wall 33 and a base rear wall 32. The base bottom wall 31 is arranged on the mounting plate left region top surface. The base bottom wall 31 is fixed to the mounting plate left region. The base bottom wall 31 is formed with a base guide hole extending in the left-right direction.
The light guide panel 4 is arranged on the top surface of the base front wall 33 and the top surface of the base rear wall 32. The light guide panel 4, the base front wall 33, the base bottom wall 31, and the base rear wall 32 together define a guide passage extending in the left-right direction. The light guide panel 4 is formed with a panel guide hole extending in the left-right direction. The light guide panel 4 can be made of aviation glass. The light guide panel 4 is hollowed out to reduce the weight thereof.
The limiting blocking piece 5 is arranged inside the guide channel. The limiting blocking piece 5 is provided with a blocking piece fixing hole. The panel guide hole, the baffle fixing hole, the bottom wall guide hole and the left area guide hole are located on the same vertical plane. Preferably, the limiting barrier 5 is formed with a barrier through hole extending in the front-rear direction. The through hole of the baffle plate is internally provided with a spring and a steel ball. The spring is arranged at the inner end, and the steel ball is arranged at the outer end. The steel balls are abutted against the base front wall 33 or the base rear wall 32.
The door control switch 6 is used for controlling the landing gear door to open and close. The hatch door control switch 6 is a toggle type electronic switch. The hatch control switch 6 is arranged below the left area of the installation plate. The hatch door control switch 6 may be fixed to the mounting plate left area by a U-shaped mounting bracket. The hatch control switch 6 has a trip vertical shaft 21. The wrenching vertical shaft 21 upwards passes through the left area guide hole, the base guide hole, the baffle fixing hole and the panel guide hole, so that the wrenching vertical shaft 21 can be wrenched leftwards and rightwards, and the wrenching vertical shaft 21 and the limiting baffle 5 synchronously act. The pulling vertical shaft 21 has at least an opening position at the left end and a closing position at the right end. In an initial state, the wrenching vertical shaft 21 is placed in the closing working position, that is, the landing gear bay door is closed, and the wrenching vertical shaft 21 drives the limiting barrier 5 to move to the right, at this time, the limiting barrier 5 is blocked in front of the wrenching handle 61 to limit the wrenching handle 61 to be wrenched forward, that is, the aircraft landing gear cannot be put down. If the wrenching vertical shaft 21 is wrenched from the closed working position to the open working position, that is, the landing gear door is opened, and the wrenching vertical shaft 21 drives the limit stop 5 to shift leftward, the block on the wrenching handle 61 is released, and the wrenching handle 61 can be wrenched forward to put down the aircraft landing gear.
The door control switch 6 is thus interlocked with the landing gear control switch 2, and the aircraft landing gear can be lowered after the landing gear door is opened.
Preferably, the hatch control switch 6 is provided with a protective cover 8. The protective cover 8 is used for preventing the pulling vertical shaft 21 from being operated by mistake.
The above description is only intended to illustrate embodiments of the present invention, and the description is specific and detailed, but not to be construed as limiting the scope of the invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several variations and modifications can be made, which are within the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.
Claims (6)
1. The emergency control undercarriage linkage protection mechanism is characterized by comprising,
the mounting plate comprises a fixed mounting plate and a fixed mounting plate, wherein the fixed mounting plate is provided with a mounting plate left area and a mounting plate right area, the mounting plate left area is provided with a left area guide hole extending along the left-right direction, and the mounting plate right area is provided with a right area guide hole extending along the front-back direction;
an undercarriage control switch for controlling the landing gear of an aircraft to be lowered, the undercarriage control switch being disposed below the mounting plate right area, the undercarriage control switch being secured to the mounting plate right area, the undercarriage control switch having a toggle handle passing upwardly through the right area guide hole, the toggle handle having at least a non-lowered work position at a rear end and a lowered work position at a front end;
the fixed base is provided with a base bottom wall, a base front wall and a base rear wall, the base bottom wall is arranged on the top surface of the left area of the installation plate, the base bottom wall is fixed on the left area of the installation plate, and the base bottom wall is provided with a base guide hole extending along the left-right direction;
the light guide panel is arranged on the top surface of the front wall of the base and the top surface of the rear wall of the base, the light guide panel, the front wall of the base, the bottom wall of the base and the rear wall of the base define a guide channel extending along the left-right direction together, and a panel guide hole extending along the left-right direction is formed in the light guide panel;
the limiting baffle is arranged in the guide channel, a baffle fixing hole is formed in the limiting baffle, and the panel guide hole, the baffle fixing hole, the bottom wall guide hole and the left area guide hole are in the same vertical plane;
the cabin door control switch is used for controlling the opening and closing of the landing gear cabin door, the cabin door control switch is arranged below the left area of the installation plate, the cabin door control switch is fixed in the left area of the installation plate, the cabin door control switch is provided with a pulling vertical shaft, and the pulling vertical shaft upwards penetrates through the left area guide hole, the base guide hole, the baffle fixing hole and the panel guide hole, so that the pulling vertical shaft can be pulled leftwards and rightwards, and synchronously acts with the limiting baffle, and the pulling vertical shaft at least has an opening working position at the left end and a closing working position at the right end;
in the initial state, the wrenching handle is arranged at the undeployed working position, the wrenching vertical shaft is arranged at the closed working position, and at the moment, the limiting blocking piece blocks the front of the wrenching handle to limit the wrenching handle to be wrenched forwards;
when the wrenching vertical shaft is wrenched from the closing working position to the opening working position, the wrenching vertical shaft drives the limiting blocking piece to move leftwards to release the blocking of the wrenching handle, so that the wrenching handle can be wrenched forwards to put down the aircraft landing gear.
2. The emergency landing gear linkage protection mechanism according to claim 1, wherein the door control switch is configured with a protective cover for preventing the wrenching vertical shaft from being misoperated.
3. The emergency landing gear linkage protection mechanism according to claim 1, wherein the limiting stopper is formed with a stopper through hole extending in the front-rear direction, the stopper through hole having a spring and a steel ball inside, wherein the spring is at an inner end, the steel ball is at an outer end, and the steel ball abuts against the base front wall or the base rear wall.
4. An emergency landing gear linkage protection mechanism according to claim 1, wherein the light guide panel is formed from aircraft glass.
5. The emergency landing gear linkage protection mechanism of claim 4, wherein the light guide panel is internally hollowed out.
6. The emergency operated landing gear linkage protection mechanism according to claim 1, wherein the door control switch is secured to the mounting plate left region by a U-shaped mounting bracket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120987279.2U CN214690153U (en) | 2021-05-10 | 2021-05-10 | Linkage protection mechanism for emergency control undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120987279.2U CN214690153U (en) | 2021-05-10 | 2021-05-10 | Linkage protection mechanism for emergency control undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214690153U true CN214690153U (en) | 2021-11-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120987279.2U Active CN214690153U (en) | 2021-05-10 | 2021-05-10 | Linkage protection mechanism for emergency control undercarriage |
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| Country | Link |
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| CN (1) | CN214690153U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116374164A (en) * | 2023-04-25 | 2023-07-04 | 南京儒一航空机械装备有限公司 | Landing gear handle mechanism of airplane |
-
2021
- 2021-05-10 CN CN202120987279.2U patent/CN214690153U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116374164A (en) * | 2023-04-25 | 2023-07-04 | 南京儒一航空机械装备有限公司 | Landing gear handle mechanism of airplane |
| CN116374164B (en) * | 2023-04-25 | 2024-03-01 | 南京儒一航空机械装备有限公司 | Landing gear handle mechanism of airplane |
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