CN220332931U - Unlocking driving device of landing gear upper lock - Google Patents
Unlocking driving device of landing gear upper lock Download PDFInfo
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- CN220332931U CN220332931U CN202223529675.4U CN202223529675U CN220332931U CN 220332931 U CN220332931 U CN 220332931U CN 202223529675 U CN202223529675 U CN 202223529675U CN 220332931 U CN220332931 U CN 220332931U
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- unlocking
- upper lock
- electric mechanism
- mounting hole
- linear electric
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- 239000000446 fuel Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model provides an unlocking driving device of an upper lock of a landing gear, which belongs to the technical field of electric mechanism design, and adopts a hydraulic actuator cylinder as a normal unlocking power source of the upper lock and a linear electric mechanism as an emergency unlocking power source, wherein the hydraulic actuator cylinder is connected with the linear electric mechanism through a lever rocker arm, so that the hydraulic actuator cylinder is used for unlocking and locking in normal work. When the hydraulic actuator cannot work, the linear electric mechanism is electrified to control the extension of the hydraulic actuator, so that unlocking can be realized, the hydraulic actuator is not required to be depressurized by controlling the operation of the selection valve by firstly electrifying the operation of the selection valve electric mechanism, the unlocking time is shortened, the unlocking reliability of the upper lock caused by single-point faults such as the fault of the selection valve electric mechanism, the fault of the selection valve or the clamping stagnation fault of the hydraulic actuator is also avoided, and the unlocking reliability of the upper lock is improved.
Description
Technical Field
The utility model belongs to the technical field of electric mechanism design, and particularly relates to an unlocking driving device of an upper lock of a landing gear.
Background
Modern aircraft take up the landing gear during flight to reduce the flight resistance, thereby improving the flight speed and reducing the fuel consumption, and then put down the landing gear before landing. The function of the landing gear upper lock is to fix the landing gear support in the retracted position, bear the weight load of the landing gear, and the upper lock should be opened firstly when the landing gear is put on, and unlocking of the upper lock is guaranteed in the first position.
When the landing gear is required to be put down in an emergency under the condition of hydraulic failure, the selection valve of the hydraulic driving mechanism of the upper lock is firstly opened by the electric mechanism of the selection valve, so that the hydraulic driving mechanism is decompressed, the hydraulic driving mechanism can move freely under the driving of external force, and the upper lock is driven to unlock by the electric mechanism of the upper lock, so that the landing gear is put down under the action of gravity and aerodynamic force.
The above-described manner has the following disadvantages: 1. the emergency unlocking time is long, and the unlocking action can be performed only by opening the selection valve, which is disadvantageous to the emergency landing gear lowering; 2. the reliability is low, the selection valve electric mechanism, the selection valve and the hydraulic driving mechanism (such as hydraulic driving mechanism clamping stagnation) are single-point fault points, and no matter the selection valve electric mechanism breaks down or the selection valve breaks down or the hydraulic driving mechanism clamping stagnation breaks down, emergency unlocking actions can not be carried out or the hydraulic system is damaged due to forced unlocking, so that the reliability of the upper lock unlocking function is seriously reduced.
Disclosure of Invention
In order to solve the problems of long emergency unlocking time and low reliability of an upper lock in the related art, the utility model provides an unlocking driving device of an upper lock of a landing gear, which comprises the following technical scheme:
an unlocking drive for an undercarriage uplock, comprising: a hydraulic actuating cylinder, a base, a lever rocker arm, a linear electric mechanism and an upper lock,
the upper lock and the base are installed and fixed on an airplane structure, the hydraulic actuating cylinder is provided with an immovable end and a first extending shaft end, the linear electric mechanism is provided with an immovable end and a second extending shaft end, the end part of the first extending shaft of the hydraulic actuating cylinder is hinged with the end part of an unlocking rocker arm of the upper lock, the middle part of the lever rocker arm is hinged with the base, the end part of the immovable end of the hydraulic actuating cylinder is hinged with one end of the lever rocker arm, the end part of the immovable end of the linear electric mechanism is hinged with the lower end of the upper lock, and the end part of the second extending shaft end of the linear electric mechanism is hinged with the other end of the lever rocker arm.
Optionally, two ends of the lever rocker arm are respectively provided with a mounting hole, the end part of the stationary end of the hydraulic actuator cylinder is hinged with one end mounting hole of the lever rocker arm, and the end part of the second extending shaft end of the linear electric mechanism is hinged with the other end mounting hole of the lever rocker arm.
Optionally, a mounting hole is formed in the middle of the lever rocker arm, and the middle mounting hole of the lever rocker arm is hinged with the base.
Optionally, the end of the stationary end of the hydraulic ram is provided with a first mounting hole.
Optionally, a third mounting hole is formed in the end portion of the fixed end of the linear electric mechanism, and the third mounting hole of the fixed end of the linear electric mechanism is hinged to the lower end of the upper lock.
Optionally, a fourth mounting hole is formed at the end of the second extending shaft of the linear electric mechanism, and the fourth mounting hole of the second extending shaft of the linear electric mechanism is hinged with the other end of the lever rocker arm.
Optionally, the uplock includes: the upper lock shell is fixedly arranged on the aircraft structure, the unlocking rocker is fixed on a driving shaft of the upper lock, a fifth mounting hole is formed in the end portion of the unlocking rocker, and the end portion of the first extending shaft of the hydraulic actuating cylinder is hinged with the fifth mounting hole on the unlocking rocker.
Optionally, a sixth mounting hole is formed in the lower end of the upper lock shell.
Optionally, the first projecting shaft end of the hydraulic ram is provided with a second mounting hole.
According to the utility model, the hydraulic actuator cylinder is used as a normal unlocking power source of the upper lock, and the linear electric mechanism is used as an emergency unlocking power source, so that the hydraulic actuator cylinder is connected with the linear electric mechanism through the lever rocker arm, and the hydraulic actuator cylinder is used for unlocking and locking in normal work. When the hydraulic actuator cannot work, the linear electric mechanism is electrified to control the extension of the hydraulic actuator, so that unlocking can be realized, the hydraulic actuator is not required to be depressurized by controlling the operation of the selection valve by firstly electrifying the operation of the selection valve electric mechanism, the unlocking time is shortened, the unlocking reliability of the upper lock caused by single-point faults such as the fault of the selection valve electric mechanism, the fault of the selection valve or the clamping stagnation fault of the hydraulic actuator is also avoided, and the unlocking reliability of the upper lock is improved.
Drawings
Fig. 1 is a schematic diagram of an unlocking driving device of a landing gear upper lock according to an embodiment of the present utility model;
fig. 2 is a schematic diagram of a normal operation of an unlocking driving device of an upper lock of a landing gear according to an embodiment of the present utility model;
fig. 3 is a schematic diagram of an emergency unlocking principle of an unlocking driving device of an upper lock of a landing gear according to an embodiment of the present utility model;
FIG. 4 is a front view of an unlocking drive for a landing gear uplock according to an embodiment of the present utility model;
FIG. 5 is a front view of an uplock according to an embodiment of the present utility model;
FIG. 6 is a front view of a linear motor provided in an embodiment of the present utility model;
FIG. 7 is a schematic view showing an extended state of an extended shaft of a linear electric mechanism according to an embodiment of the present utility model;
FIG. 8 is a front view of a hydraulic ram provided in an embodiment of the present utility model;
fig. 9 is a schematic view showing an extended state of an extended shaft of a hydraulic actuator according to an embodiment of the present utility model.
The hydraulic cylinder comprises a 1-hydraulic cylinder, a 2-base, a 3-lever rocker arm, a 4-linear electric mechanism, a 5-upper lock, a first mounting hole at the non-moving end of the 11-hydraulic cylinder, a 12-hydraulic cylinder body, a first extending shaft of the 13-hydraulic cylinder, a second mounting hole on the extending shaft of the 14-hydraulic cylinder, a third mounting hole at the non-moving end of the 41-linear electric mechanism, a 42-linear electric mechanism body, a second extending shaft of the 43-linear electric mechanism, a fourth mounting hole on the extending shaft of the 44-linear electric mechanism, a 51-unlocking rocker arm, a fifth mounting hole on the 52-unlocking rocker arm, a 53-upper lock shell and a sixth mounting hole on the 54-upper lock shell.
Detailed Description
The utility model is described in further detail below with reference to specific embodiments and figures.
The utility model provides an unlocking driving device of an upper lock of a landing gear, referring to fig. 4, comprising: a hydraulic actuator cylinder 1, a base 2, a lever rocker arm 3, a linear electric mechanism 4 and an upper lock 5,
the upper lock 5 and the base 2 are fixedly arranged on an airplane structure, the hydraulic actuator cylinder 1 is provided with a fixed end and a first extending shaft 13 end, the linear electric mechanism 4 is provided with a fixed end and a second extending shaft 43 end, the end of the first extending shaft 13 of the hydraulic actuator cylinder 1 is hinged with the end of an unlocking rocker arm 51 of the upper lock 5, the middle part of the lever rocker arm 3 is hinged with the base 2, the lever rocker arm 3 can do seesaw type swinging motion around the hinged position, the end of the fixed end of the hydraulic actuator cylinder 1 is hinged with one end of the lever rocker arm 3, the end of the fixed end of the linear electric mechanism 4 is hinged with the lower end on the upper lock housing 53, and the end of the second extending shaft 43 end of the linear electric mechanism 4 is hinged with the other end of the lever rocker arm 3.
In another embodiment, as shown in fig. 6, the linear electric mechanism 4 is configured such that the linear electric mechanism body 42 of the linear electric mechanism 4 has both a stationary end and an extended shaft end, and the linear electric mechanism 4 is a typical industrial element, and the second extended shaft 43 of the linear electric mechanism 4 can be electrically controlled to extend and retract relative to the linear electric mechanism body 42, i.e., the linear electric mechanism 4 can be lengthened or shortened. Fig. 6 shows the second extension shaft 43 of the linear motor 4 in the retracted state, and fig. 7 shows the second extension shaft 43 of the linear motor 4 in the extended state.
After the second extension shaft 43 of the linear electric mechanism 4 is extended and retracted into place, unless the second extension shaft 43 of the linear electric mechanism 4 is energized to control the retraction of the second extension shaft 43 from the extended state and the extension after the retraction into place, the linear electric mechanism 4 can be maintained in the extended into place state or the retracted into place state of the second extension shaft 43, i.e., the state of the second extension shaft 43 of the linear electric mechanism 4 cannot be changed by an external force, and the linear electric mechanism 4 is in the self-locking state.
The stationary end of the linear motor 4 is provided with a third mounting hole 41, and the second projecting shaft 43 of the linear motor 4 is provided with a fourth mounting hole 44.
The structure of the uplock 5 is shown in fig. 5, the uplock 5 comprises an uplock housing 53 and an unlocking rocker arm 51, the uplock housing 53 of the uplock 5 is fixedly arranged on the aircraft structure, the unlocking rocker arm 51 is fixedly arranged on a driving shaft of the uplock 5, and the unlocking rocker arm 51 can swing around the swinging center to drive the uplock to unlock. Fig. 5 shows that the upper lock 5 is in a locked state, the unlocking rocker arm 51 can swing clockwise from the unlocked state shown in fig. 5 under the driving of an external force to unlock, and after the unlocking is in place, the unlocking rocker arm 51 can swing counterclockwise to the state shown in fig. 5 under the driving of the external force to unlock. The lock housing 53 is provided with a sixth mounting hole 54, and the unlocking rocker 51 is provided with a fifth mounting hole 52.
The structure of the hydraulic actuator 1 is shown in fig. 8, the hydraulic actuator body 12 of the hydraulic actuator 1 is provided with a non-actuating end and an extending shaft end which are commonly provided, the hydraulic actuator 1 is used as a typical industrial element, the first extending shaft 13 of the hydraulic actuator 1 can be controlled to extend and retract relative to the hydraulic actuator body 12 through hydraulic driving, fig. 8 shows the first extending shaft 13 of the hydraulic actuator 1 in a retracted state, fig. 9 shows the first extending shaft 13 of the hydraulic actuator 1 in an extended state, and after the first extending shaft 13 of the hydraulic actuator 1 is retracted in place, the length of the hydraulic actuator 1 cannot be compressed. The stationary end of the hydraulic ram 1 has a first mounting hole 11 and the first extension shaft 13 of the hydraulic ram 1 has a second mounting hole 14.
As shown in fig. 4, the upper lock 5 and the base 2 are mounted and fixed on the aircraft structure, the second mounting hole 14 on the first projecting shaft 13 of the hydraulic actuator 1 is hinged to the fifth mounting hole 52 on the unlocking rocker arm 51 of the upper lock 5, the lever rocker arm 3 has a common end a (the upper end of the lever rocker arm 3 shown in fig. 4) and a common end B (the lower end of the lever rocker arm 3 shown in fig. 4), the a end and the B end of the lever rocker arm 3 each have a mounting hole, the lever rocker arm 3 is hinged to the base 2 through the mounting hole in the middle position, so that the lever rocker arm 3 can make a seesaw-type swinging motion around the mounting hole, the first mounting hole 11 of the stationary end of the hydraulic actuator 1 is hinged to the mounting hole a end of the lever rocker arm 3, the third mounting hole 41 of the stationary end of the linear electric mechanism 4 is hinged to the sixth mounting hole 54 on the housing of the upper lock 5, and the fourth mounting hole 44 of the second projecting shaft end of the linear electric mechanism 4 is hinged to the lever rocker arm 3.
The hinge is realized by adopting a matching mode of the mounting hole and the insert, wherein the insert can be a screw or a bolt. In addition, other hinge structures may be used, which are not limited thereto.
A schematic block diagram of an unlocking driving device of a landing gear upper lock, which is formed by components in fig. 4, is shown in fig. 1. In fig. 1, the upper lock 5 is in the locked state, the linear electric mechanism 4 is not operated and is in the retracted self-locking state, and the lever rocker arm 3 is also in the fixed state because the length of the linear electric mechanism 4 is fixed.
As shown in fig. 2, when the upper lock 5 is in the locked state, the hydraulic actuator 1 is hydraulically driven to move from the retracted state shown in the drawing to the extended state, and the unlocking rocker 51 of the upper lock 5 swings clockwise shown in the drawing, thereby completing the unlocking operation of the upper lock 5 which normally operates; when the uplock 5 is in the unlock state, the hydraulic actuator 1 is hydraulically driven to move from the extended state shown in the drawing to the retracted state, and the unlock rocker arm 51 of the uplock 5 swings counterclockwise shown in the drawing, thereby completing the locking operation of the uplock 5 that normally operates.
As shown in fig. 3, when the upper lock 5 is in the locked state and the hydraulic cylinder 1 fails and cannot operate, the hydraulic cylinder 1 is in the retracted state and cannot be compressed in length, the extension shaft of the linear electric mechanism 4 is controlled to move from the illustrated retracted state to the extended state by energization, the lever rocker 3 is driven to swing clockwise along the installation Kong of the middle position, the lever rocker 3 is driven to move wholly rightward by the hydraulic cylinder 1, and the unlocking rocker 51 of the upper lock 5 is driven to swing clockwise in the illustration, so that the emergency unlocking action of the upper lock 5 is completed.
The foregoing has outlined rather broadly the more detailed description of the utility model in order that the detailed description thereof that follows may be better understood, and in order that the present utility model may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the utility model, which are all within the scope of the utility model. In addition, the utility model is not fully described in the conventional technology.
Claims (9)
1. An unlocking drive for an upper landing gear lock, comprising: a hydraulic actuating cylinder (1), a base (2), a lever rocker arm (3), a linear electric mechanism (4) and an upper lock (5),
the upper lock (5) and the base (2) are installed and fixed on an airplane structure, the hydraulic actuating cylinder (1) is provided with a fixed end and a first extending shaft (13) end, the linear electric mechanism (4) is provided with a fixed end and a second extending shaft (43) end, the end of the first extending shaft (13) of the hydraulic actuating cylinder (1) is hinged with the end of an unlocking rocker (51) of the upper lock (5), the middle part of the lever rocker (3) is hinged with the base (2), the end of the fixed end of the hydraulic actuating cylinder (1) is hinged with one end of the lever rocker (3), the end of the fixed end of the linear electric mechanism (4) is hinged with the lower end of the upper lock (5), and the end of the second extending shaft (43) of the linear electric mechanism (4) is hinged with the other end of the lever rocker (3).
2. The apparatus of claim 1, wherein the device comprises a plurality of sensors,
the two ends of the lever rocker arm (3) are respectively provided with a mounting hole, the end part of the stationary end of the hydraulic actuator cylinder (1) is hinged with one end mounting hole of the lever rocker arm (3), and the end part of the second extension shaft (43) end of the linear electric mechanism (4) is hinged with the other end mounting hole of the lever rocker arm (3).
3. The apparatus of claim 2, wherein the device comprises a plurality of sensors,
the middle part of the lever rocker arm (3) is provided with a mounting hole, and the middle mounting hole of the lever rocker arm (3) is hinged with the base (2).
4. The apparatus of claim 1, wherein the device comprises a plurality of sensors,
the end part of the stationary end of the hydraulic actuator cylinder (1) is provided with a first mounting hole (11).
5. The apparatus of claim 1, wherein the device comprises a plurality of sensors,
the end part of the stationary end of the linear electric mechanism (4) is provided with a third mounting hole (41), and the third mounting hole (41) of the stationary end of the linear electric mechanism (4) is hinged with the lower end of the upper lock (5).
6. The apparatus of claim 5, wherein the device comprises a plurality of sensors,
a fourth mounting hole (44) is formed in the end portion of the second extending shaft (43) of the linear electric mechanism (4), and the fourth mounting hole (44) of the second extending shaft (43) of the linear electric mechanism (4) is hinged to the other end of the lever rocker arm (3).
7. The apparatus of claim 1, wherein the device comprises a plurality of sensors,
the upper lock (5) comprises: the upper lock comprises an upper lock shell (53) and an unlocking rocker arm (51), wherein the upper lock shell (53) is installed and fixed on an airplane structure, the unlocking rocker arm (51) is fixed on a driving shaft of the upper lock (5), a fifth mounting hole (52) is formed in the end portion of the unlocking rocker arm (51), and the end portion of a first extension shaft (13) of the hydraulic actuator cylinder (1) is hinged to the fifth mounting hole (52) on the unlocking rocker arm (51).
8. The apparatus of claim 7, wherein the device comprises a plurality of sensors,
the lower end of the upper lock shell (53) is provided with a sixth mounting hole (54).
9. The apparatus of claim 1, wherein the device comprises a plurality of sensors,
the end part of the first extension shaft (13) of the hydraulic actuator cylinder (1) is provided with a second mounting hole (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223529675.4U CN220332931U (en) | 2022-12-29 | 2022-12-29 | Unlocking driving device of landing gear upper lock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223529675.4U CN220332931U (en) | 2022-12-29 | 2022-12-29 | Unlocking driving device of landing gear upper lock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220332931U true CN220332931U (en) | 2024-01-12 |
Family
ID=89450503
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223529675.4U Active CN220332931U (en) | 2022-12-29 | 2022-12-29 | Unlocking driving device of landing gear upper lock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220332931U (en) |
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2022
- 2022-12-29 CN CN202223529675.4U patent/CN220332931U/en active Active
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