CN219096977U - Automatic throttle on-off limiting device for civil aircraft - Google Patents

Abstract

The utility model belongs to the technical field of civil aircraft assembly manufacturing and test, and discloses an automatic throttle on-off limiting device of a civil aircraft, which comprises two wall plates and a limiting stop rod, wherein the two wall plates are parallel to each other and are arranged at intervals, the two wall plates are fixedly connected to a throttle table, and ratchet teeth of a ratchet mechanism are arranged on the wall plates; the two ends of the limit stop rod are respectively provided with a pawl of the ratchet mechanism, and the pawl is meshed with the ratchet teeth to lock the limit stop rod. According to the utility model, the ratchet wheel teeth of the ratchet mechanism are arranged on the wallboard, the pawls of the ratchet mechanism are arranged at the two ends of the limiting stop rod, so that the pawls can be meshed and locked with the ratchet wheel teeth, and the limiting stop rod is provided with limiting resistance far greater than the internal driving force of the accelerator table by utilizing rigid static friction between the pawls and the ratchet wheel teeth, so that a reliable limiting effect under the working condition of automatic accelerator function test is realized.

Description

Automatic throttle on-off limiting device for civil aircraft

Technical Field

The utility model relates to the technical field of civil aircraft assembly manufacturing and test, in particular to an automatic throttle on-off limiting device of a civil aircraft.

Background

The automatic throttle is a full-right throttle control technology of a full-flight envelope for maintaining a target speed or target thrust, can provide visual thrust guidance and automatic throttle control of the full-flight envelope to maintain the target speed or target thrust, and provides fault monitoring and visual/acoustic information to ensure the health state of an automatic thrust system. The automatic throttle drives the throttle lever through the servo back-driving motor, so that the thrust tracks the throttle instruction calculated by the thrust guide, and the throttle lever is driven to keep the target speed or the reference thrust to move at full speed in the stroke range of the throttle lever, so that the automatic flight control of the aircraft is realized in a mode of automatically controlling the thrust of the engine, the whole process has the full-authority override characteristic, and once the automatic throttle is switched on, the capability of manually overriding the throttle lever by an operator without switching off the automatic throttle is provided.

In the prior art, aiming at the automatic throttle function of an automatic flight control system, the conventional test method is to switch on an automatic throttle switch under the slow-running state of an airplane, trigger automatic throttle control pre-positioning, activate the automatic throttle function on site through modes such as airplane air state simulation, attack angle platform thrust mode simulation, throttle push-to-switch-on door limit and the like, enable an throttle lever to maintain the target speed or target thrust of the throttle lever by means of a full-right throttle control instruction of a full-flight envelope, and realize the override operation of the throttle lever until reaching the limit position of the current environment of the throttle lever, and visually observe the automatic forward push phenomenon of the throttle lever by an operator in the test process so as to characterize the effectiveness of the automatic throttle function.

In the automatic throttle function test process, because the automatic forward pushing process of the throttle lever is a full-right override process for keeping the full-speed movement of the target speed or the reference thrust, if no manual strong intervention exists, or an operator fails to timely switch off the automatic throttle function by manually switching off the automatic throttle switch in the cockpit, the throttle lever can not limit full speed to reach the limit deviation position of the throttle table. When a large wind speed exists on a test site, or a wheel resident brake fault exists, or an engine test wheel block is worn and aged, the aircraft can overcome static friction force between the wheel and the ground, simultaneously overcome electromagnetic stop resistance of the wheel brake, unexpected sliding occurs, and when serious, the aircraft can rush out of the test site to impact a test wheel block, so that serious production accidents are caused.

Meanwhile, the existing test mode, namely the test process for characterizing the effectiveness of the automatic throttle function by visually observing the automatic forward pushing phenomenon of the throttle lever by an operator, has the problems that the test phenomenon is difficult to capture and the like, has lower visual resolution of human eyes, and has the problems that the test result is influenced by the artificial reaction time and the judgment error, and the test verification in a plurality of open states is also wasteful of on-site production resources.

Disclosure of Invention

The utility model aims to provide an automatic throttle on-off limiting device for a civil aircraft, which aims to solve the problem that limiting deflection movement of a throttle lever is not limited in the automatic throttle test process.

To achieve the purpose, the utility model adopts the following technical scheme:

automatic throttle break-make stop device of civil aircraft includes:

the two wallboards are arranged in parallel and at intervals, the two wallboards are fixedly connected to the accelerator table, and ratchet teeth of a ratchet mechanism are arranged on the wallboards;

the two ends of the limiting stop rod are respectively provided with a pawl of the ratchet mechanism, and the pawls are meshed with the ratchet teeth to lock the limiting stop rod.

Optionally, the limit stop lever includes:

the two ends of the main rod body are respectively provided with blind holes;

the two elastic pieces are arranged in the two blind holes respectively;

the swing rod, the one end fixed connection of swing rod in the body of rod, the swing rod has fretwork portion, fretwork portion with the blind hole intercommunication sets up, the pawl locate in the fretwork portion and rotate connect in the swing rod, the both ends of elastic component stop respectively in the body of rod with the pawl, make the pawl keep away from the tip of the body of rod can with the spacing locking of ratchet teeth of a cogwheel.

Optionally, a film pressure sensor is arranged on the inner wall of the blind hole.

Optionally, a chute is arranged on the wall plate, the chute and the ratchet teeth are coaxially arranged, a sliding block is arranged at one end of the swing rod, which is far away from the main rod body, and the sliding block is in sliding connection in the chute.

Optionally, a boss is disposed on a side of the swing rod facing away from the ratchet teeth, the boss has a first through hole, the pawl is provided with a second through hole, and the rotating shaft is disposed in the first through hole and the second through hole in a penetrating manner so as to rotationally connect the pawl to the swing rod, so that the pawl can rotate relative to the swing rod to be unlocked or locked to the ratchet teeth.

Optionally, a flexible film is arranged on the side surface of the wall plate connected with the throttle table and/or the peripheral wall of the main rod body.

Optionally, the automatic throttle on-off limiting device of the civil aircraft further comprises a shell, wherein the shell is positioned on the outer side of the wallboard and is arranged at intervals with the wallboard, a containing cavity is formed between the shell and the wallboard, and the ratchet mechanism is arranged in the containing cavity.

Optionally, the automatic throttle on-off limiting device of the civil aircraft further comprises an acousto-optic warning component, wherein the acousto-optic warning component is arranged on the outer side of the shell, and the film pressure sensor is in communication connection with the acousto-optic warning component.

Optionally, the acousto-optic warning subassembly includes bee calling organ, display lamp, battery pack and throttle lever thrust value judgement module, battery pack electricity respectively connect bee calling organ display lamp with throttle lever thrust value judgement module is in order to provide the electric energy, film pressure sensor bee calling organ with the display lamp communicates respectively and connects throttle lever thrust value judgement module.

Optionally, the shell and the wall plate are detachably connected.

The utility model has the beneficial effects that:

according to the automatic throttle on-off limiting device of the civil aircraft, the ratchet wheel teeth of the ratchet mechanism are arranged on the wallboard, the pawls of the ratchet mechanism are arranged at the two ends of the limiting stop rod, so that the pawls can be meshed with the ratchet wheel teeth for locking, and the limiting stop rod is provided with limiting resistance far greater than the internal driving force of the throttle table by utilizing the rigid static friction between the pawls and the ratchet wheel teeth, so that a reliable limiting effect under the automatic throttle function test working condition is realized. The ratchet mechanism is used for locking and limiting, so that the accelerator table testing work with multiple working conditions and different limiting requirements is conveniently realized, and the field testing efficiency is improved.

Drawings

FIG. 1 is a schematic diagram of a civil aircraft automatic throttle on-off limiting device according to an embodiment of the utility model;

fig. 2 is a perspective view of a top view of an automatic throttle on-off limiting device of a civil aircraft provided by an embodiment of the utility model;

fig. 3 is a schematic structural view of a main rod body and a swing rod in the automatic throttle on-off limiting device of the civil aircraft provided by the embodiment of the utility model;

fig. 4 is a schematic structural view of a pawl in an automatic throttle on-off limiting device of a civil aircraft provided by the embodiment of the utility model;

fig. 5 is a schematic diagram of installation positions of a shell and an acousto-optic warning component in an automatic throttle on-off limiting device of a civil aircraft provided by the embodiment of the utility model.

In the figure:

1. a wall plate; 11. a chute;

2. a limit stop lever; 21. a main rod body; 211. a blind hole; 22. an elastic member; 23. swing rod; 231. a hollowed-out part; 232. a boss; 233. a first through hole; 234. a slide block; 24. a membrane pressure sensor;

3. ratchet wheel teeth; 4. a pawl; 41. a second through hole; 5. a housing; 6. an audible and visual alarm component; 7. and (5) sealing plates.

Detailed Description

The utility model is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present utility model are shown in the drawings.

In the description of the present utility model, unless explicitly stated and limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present utility model will be understood in specific cases by those of ordinary skill in the art.

In the present utility model, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.

In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like are orientation or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of operation, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the utility model. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for distinguishing between them.

The utility model provides an automatic throttle on-off limiting device of a civil aircraft, which is used for solving the problems that full-speed limit deflection of a throttle lever is not limited in the automatic throttle function test process, the test phenomenon of the automatic throttle function is difficult to accurately capture through human vision, necessary warning reminding is not needed after the throttle lever reaches controllable deflection, and the like.

As shown in fig. 1, the automatic throttle on-off limiting device for the civil aircraft provided by the embodiment of the utility model comprises two wall plates 1 and limiting stop rods 2, wherein the two wall plates 1 are parallel to each other and are arranged at intervals, the two wall plates 1 are fixedly connected to a throttle table, and ratchet wheel teeth 3 of a ratchet mechanism are arranged on the wall plates 1; the two ends of the limit stop lever 2 are respectively provided with a pawl 4 of a ratchet mechanism, and the pawl 4 is meshed with the ratchet teeth 3 to lock the limit stop lever 2.

It should be explained that the two wall plates 1 are oppositely arranged and symmetrically installed on the accelerator table, the installation mode and the installation position are installed according to the structure and the designated position of the accelerator table, which are generally known, and the present embodiment does not do unfolding limiting explanation. The ratchet mechanism is provided with two ratchet mechanisms which are symmetrically arranged at two ends of the limiting stop rod 2 respectively, the limiting stop rod 2 is connected with the wallboard 1 through the ratchet mechanism, and the locking and limiting of the limiting stop rod 2 under the specified test working condition are realized by utilizing the self-locking performance of the ratchet mechanism. According to the automatic throttle on-off limiting device for the civil aircraft, the plurality of ratchet wheel teeth 3 are arranged on the side face of the wallboard 1, the plurality of ratchet wheel teeth 3 form a section of arc-shaped ratchet wheel, the ratchet wheel teeth 3 of the ratchet mechanism are arranged on the wallboard 1, and the pawls 4 of the ratchet mechanism are arranged at the two ends of the limiting stop lever 2, so that the pawls 4 can be engaged with the ratchet wheel teeth 3 for locking, and the limiting stop lever 2 is provided with limiting resistance far greater than the driving force in a throttle table by utilizing rigid static friction between the pawls 4 and the ratchet wheel teeth 3, so that a reliable limiting effect under an automatic throttle function test working condition is realized, and the problem that full-speed limit deflection of the throttle lever is not limited is solved. The ratchet mechanism is used for locking and limiting, so that the locking position of the pawl 4 on the ratchet gear teeth 3 can be conveniently switched, the test work of the throttle table with multiple working conditions and different limiting requirements is realized, and the field test efficiency is improved.

Optionally, the limit stop lever 2 comprises a main lever body 21, an elastic piece 22 and a swing rod 23, and blind holes 211 are respectively formed at two ends of the main lever body 21; the number of the elastic pieces 22 is two, and the two elastic pieces 22 are respectively arranged in the two blind holes 211; one end of the swing rod 23 is fixedly connected to the main rod body 21, the swing rod 23 is provided with a hollowed-out portion 231, the hollowed-out portion 231 is communicated with the blind hole 211, the pawl 4 is arranged in the hollowed-out portion 231 and is rotationally connected to the swing rod 23, two ends of the elastic piece 22 are respectively abutted to the main rod body 21 and the pawl 4, and therefore the end portion, far away from the main rod body 21, of the pawl 4 can be locked with the ratchet wheel teeth 3 in a limiting mode.

In this embodiment, the elastic member 22 employs two springs, one end of the elastic member 22 is disposed in the blind hole 211 and abuts against the main rod 21, and the other end abuts against the pawl 4 at the opening of the blind hole 211, so that one end of the pawl 4 facing away from the elastic member 22 is engaged with the ratchet teeth 3 under the elastic force of the elastic member 22 for self-locking. It should be noted that, as shown in fig. 1-3, the ratchet teeth 3 are machined on a protruding platform on the side surface of the wall plate 1, when the pawl 4 does not swing or rotate, the pawl 4 is completely embedded in the hollowed-out portion 231, the swing rod 23 can drive the pawl 4 to swing on the protruding platform, when the pawl 4 swings to a required limit position, the elastic piece 22 provides a pressing force for the pawl 4, the elastic piece 22 of the pawl 4 rotates relative to the swing rod 23 under the elastic action of the elastic piece 22, so that one end of the pawl 4 away from the main rod 21 rotates towards one side of the ratchet teeth 3 and is engaged with the ratchet teeth 3. It can be understood that the pawl 4 does not rotate and is located in the hollow portion 231 only when the elastic force of the elastic member 22 is overcome manually, and in the installed static state, the pawl 4 is always locked to the ratchet teeth 3 under the elastic force of the elastic member 22, so as to lock the limit stop lever 2 relative to the wall plate 1, so as to facilitate multi-working condition test of different locking positions. The ratchet mechanism is adopted for adjusting the limiting position, the structure is simple, the expansibility is good, the limiting working conditions of various operating devices can be adapted, the implementation mode can be flexibly changed according to different control and requirements, the device can be widely applied to limiting scenes of an operating system for aviation manufacturing, and the device has a large popularization value. During the test, the elastic piece 22 is compressed to adjust the swing rod 23 and the pawl 4 to the target position, the elastic piece 22 is loosened, the pawl 4 is locked on the ratchet wheel teeth 3 under the elastic action of the elastic piece 22 to form a ratchet mechanism, the locking state of the limiting stop lever 2 is achieved, the stop pawl 4 is restrained by the ratchet wheel teeth 3 and cannot exceed the target limiting position which is adjusted, and the limiting function of the throttle lever is realized.

Optionally, a boss 232 is disposed on a side of the swing rod 23 facing away from the ratchet teeth 3, the boss 232 has a first through hole 233, the pawl 4 is provided with a second through hole 41, and a rotating shaft is disposed in the first through hole 233 and the second through hole 41 in a penetrating manner to rotationally connect the pawl 4 to the swing rod 23, so that the pawl 4 can rotate relative to the swing rod 23 to be unlocked or locked to the ratchet teeth 3.

As shown in fig. 3 and 4, the boss 232 is symmetrically disposed at two sides of the hollowed-out portion 231, the second through hole 41 on the pawl 4 is located between the two first through holes 233 and is coaxial, the rotating shaft can sequentially pass through the first through holes 233 and the second through holes 41 to rotate and connect the pawl 4, one end of the pawl 4 rotates towards a direction away from the wall plate 1 under the action of the elastic piece 22, and the other end rotates towards the wall plate 1 so as to facilitate the engagement and locking of the ratchet teeth 3. It will be appreciated that by providing the first through hole 233 on the boss 232, it is advantageous to increase the rotational angle of the pawl 4 so as to provide better locking stability. Preferably, the shape of the pawl 4 is matched with the shape of the hollowed-out part 231, the thickness of the swing rod 23 is equal to that of the pawl 4, and the pawl 4 can rotate and mesh with the ratchet wheel teeth 3 under the action of the elastic force of the smaller elastic piece 22, so that larger rigid friction resistance is provided.

Alternatively, the outer peripheral wall of the main rod body 21 is provided with a film pressure sensor 24.

As shown in fig. 2, the film pressure sensor 24 is arranged around the outer peripheral wall of the main rod body 21, so that the thrust value of the limit stop lever 2 can be monitored and detected in real time, the problem of overrun deflection of the throttle lever can be timely relieved by a cockpit operator, and the safety of the aircraft in the testing process is improved.

Optionally, a sliding groove 11 is formed in the wall plate 1, the sliding groove 11 and the ratchet wheel teeth 3 are coaxially arranged, a sliding block 234 is arranged at one end, away from the main rod body 21, of the swing rod 23, and the sliding block 234 is slidably connected in the sliding groove 11.

As shown in fig. 1 and 3, the arc surfaces of the chute 11 and the ratchet teeth 3 are concentric arcs and have the same central angle, when the sliding block 234 slides in the chute 11, the pawl 4 can be meshed with the ratchet teeth 3 at a plurality of different positions to stop so as to stop and lock, the chute 11 provides a rotation plane for the swing rod 23 to stop, so that the swing rod 23 can always abut against a convex platform where the ratchet teeth 3 are located to slide in a rotation manner, and stable locking and unlocking of the pawl 4 and the ratchet teeth 3 can be ensured.

Optionally, flexible adhesive films are provided on the side surface of the wall plate 1 connected with the throttle table and/or the peripheral wall of the main rod body 21.

As shown in fig. 1 and 2, the two opposite inner side surfaces of the two wall plates 1 are provided with flexible films, the outer peripheral wall of the main rod body 21 is provided with a flexible film, and the film pressure sensor 24 is provided between the outer wall of the main rod body 21 and the flexible film. In this embodiment, wallboard 1 and the body of rod 21 all adopt light aluminum alloy material, and the effect of flexible pad pasting is the protection contact position on the wallboard 1, like the surface of throttle platform body and throttle platform manipulation structure surface, can greatly reduce equipment damage risk, under the prerequisite that satisfies spacing demand, improves test process security. The flexible film is arranged on the peripheral wall of the main rod body 21 to provide external protection for the accelerator table operating mechanism, avoid equipment damage caused by collision between the accelerator rod and the limiting stop rod 2 and block the automatic forward pushing movement of the accelerator rod of the target equipment. Wherein the flexible film is a latex film.

Optionally, the automatic throttle on-off limiting device of the civil aircraft further comprises a shell 5, wherein the shell 5 is positioned on the outer side of the wallboard 1 and is arranged at intervals with the wallboard 1, a containing cavity is formed between the shell 5 and the wallboard 1, and the ratchet mechanism is arranged in the containing cavity.

As shown in fig. 5, two shells 5 are arranged and are in one-to-one correspondence with two wall plates 1, the shells 5 are arranged on the outer sides of the wall plates 1 and are fixedly connected with the wall plates 1, a containing cavity is formed between the wall plates 1 and the shells 5, the opening of the containing cavity meets the rotation limit requirements of the pawl 4 at different positions on the ratchet teeth 3, the rest part of the containing cavity is of a sealing structure, the ratchet mechanism is arranged in the containing cavity, and the damage of other parts in the testing equipment caused by falling of the parts in the ratchet mechanism can be avoided. In this embodiment, the distance between the housing 5 and the wall plate 1 is the width of the accommodating cavity, the width of the accommodating cavity needs to meet the rotation space requirement of the pawl 4, and the axial displacement of the swing rod 23 or the main rod body 21 can be limited in a certain range, so that the pawl 4 can rotate in place, and the locking is stable and reliable. The outer shell 5 can provide external protection for the whole device, and as the device outer shell 5, the device outer shell 5 not only has the protection function of blocking external sundries from entering the ratchet mechanism, but also can be provided with a position indication line on the outer shell 5 for identifying the limiting position of the limiting stop lever 2. The common limiting clamping information of the limiting stop lever 2 is marked on the shell 5, and the limiting information of the limiting stop lever 2 under the conventional working condition on site is indicated, so that the test efficiency is improved.

Optionally, the automatic throttle on-off limiting device of the civil aircraft further comprises an acousto-optic alarm assembly 6, wherein the acousto-optic alarm assembly 6 is arranged on the outer side of one shell 5, and the film pressure sensor 24 is in communication connection with the acousto-optic alarm assembly 6.

As shown in fig. 5, the acousto-optic alarm component 6 is used for providing alarm prompts of sound and light, feeding back the pressure value of the film pressure sensor 24, and the thrust real-time monitoring system composed of the film pressure sensor 24 and the acousto-optic alarm component 6 can monitor the thrust value of the throttle lever in real time, so that the safety of the airplane in the test process is improved.

Optionally, the audible and visual alarm assembly 6 includes a buzzer, a display lamp, a battery assembly and a throttle lever thrust value judging module, where the battery assembly is electrically connected to the buzzer, the display lamp and the throttle lever thrust value judging module respectively to provide electric energy, and the film pressure sensor 24, the buzzer and the display lamp are connected to the throttle lever thrust value judging module respectively in communication.

The throttle lever thrust value judging module is used for collecting the detection value of the film pressure sensor 24 and comparing and judging with a threshold value, if the actual thrust, i.e. the detection value, is greater than the threshold value, the acousto-optic warning component 6 triggers warning, including red light on, green light off and buzzer repeated out-of-limit warning, so as to remind a cockpit operator of timely relieving the problem of throttle lever out-of-limit deflection. And when the thrust value of the throttle lever is smaller than the threshold value, the alarm is released, the green light is on, the red light is off, and the buzzer does not sound.

Optionally, the housing 5 is detachably connected to the wall plate 1. In this embodiment, the bolts are used to connect, and meanwhile, the sealing plate 7 is used to seal the opening of the accommodating cavity between the housing 5 and the wall plate 1, two ends of the opening of the accommodating cavity are slightly larger than two ends of the ratchet teeth 3 respectively, and when the limit stop lever 2 is at the initial position or the target limit position, the sealing plate 7 can further ensure limit position limitation of the throttle stop lever 2, so that the occurrence of over-position damage is avoided.

According to the automatic throttle on-off limiting device for the civil aircraft, provided by the embodiment of the utility model, the position of the limiting stop lever 2 is locked by the ratchet mechanism, so that the human eye vision capturing automatic throttle function test phenomenon is converted into mechanical limiting representation, errors caused by manual judgment in the test process are reduced, and the automatic throttle function test result can be scientifically captured on the basis of ensuring the safety of the aircraft according to whether the throttle lever reaches the target limit as a criterion of the test result. The automatic throttle on-off limiting device of the civil aircraft has good expansibility, changes the appearance of the limiting device based on different target devices, can adapt to the limiting working conditions of various operating devices, is simple in mechanism and strong in universality, and can be widely popularized and applied to limiting links of an operating system in aviation manufacturing.

It is to be understood that the above examples of the present utility model are provided for clarity of illustration only and are not limiting of the embodiments of the present utility model. Various obvious changes, rearrangements and substitutions can be made by those skilled in the art without departing from the scope of the utility model. It is not necessary here nor is it exhaustive of all embodiments. Any modification, equivalent replacement, improvement, etc. which come within the spirit and principles of the utility model are desired to be protected by the following claims.

Claims (10)

1. Automatic throttle break-make stop device of civil aircraft, its characterized in that includes:

the accelerator pedal comprises two wall plates (1), wherein the two wall plates (1) are parallel to each other and are arranged at intervals, the two wall plates (1) are fixedly connected to the accelerator pedal, and ratchet gear teeth (3) of a ratchet mechanism are arranged on the wall plates (1);

the ratchet mechanism comprises a limiting stop rod (2), wherein pawls (4) of the ratchet mechanism are respectively arranged at two ends of the limiting stop rod (2), and the pawls (4) are meshed with ratchet teeth (3) to lock the limiting stop rod (2).

2. The civil aircraft automatic throttle on-off limiting device according to claim 1, characterized in that the limiting lever (2) comprises:

the device comprises a main rod body (21), wherein blind holes (211) are respectively formed at two ends of the main rod body (21);

the elastic pieces (22) are arranged, the two elastic pieces (22) are arranged, and the two elastic pieces (22) are respectively arranged in the two blind holes (211);

the swing rod (23), the one end fixed connection of swing rod (23) in the body of rod (21), swing rod (23) have fretwork portion (231), fretwork portion (231) with blind hole (211) intercommunication sets up, pawl (4) locate in fretwork portion (231) rotate connect in swing rod (23), the both ends of elastic component (22) end respectively prop against in the body of rod (21) with pawl (4), make pawl (4) keep away from the tip of body of rod (21) can with spacing locking of ratchet teeth (3).

3. The automatic throttle on-off limiting device of civil aircraft according to claim 2, characterized in that the inner wall of the blind hole (211) is provided with a film pressure sensor (24).

4. The automatic throttle on-off limiting device of civil aircraft according to claim 2, wherein a chute (11) is arranged on the wall plate (1), the chute (11) and the ratchet wheel teeth (3) are coaxially arranged, a sliding block (234) is arranged at one end of the swing rod (23) far away from the main rod body (21), and the sliding block (234) is slidably connected in the chute (11).

5. The automatic throttle on-off limiting device of civil aircraft according to claim 2, wherein a boss (232) is arranged on one side of the swing rod (23) away from the ratchet wheel teeth (3), the boss (232) is provided with a first through hole (233), the pawl (4) is provided with a second through hole (41), and a rotating shaft is arranged in the first through hole (233) and the second through hole (41) in a penetrating manner so as to rotationally connect the pawl (4) to the swing rod (23), so that the pawl (4) can rotate relative to the swing rod (23) to be unlocked or locked on the ratchet wheel teeth (3).

6. The automatic throttle on-off limiting device of civil aircraft according to claim 2, characterized in that flexible adhesive films are arranged on the side surface of the wall plate (1) connected with the throttle table and/or the peripheral wall of the main rod body (21).

7. The automatic throttle on-off limiting device for the civil aircraft according to claim 3, further comprising a housing (5), wherein the housing (5) is located on the outer side of the wall plate (1) and is arranged at intervals with the wall plate (1), a containing cavity is formed between the housing (5) and the wall plate (1), and the ratchet mechanism is arranged in the containing cavity.

8. The automatic throttle on-off limiting device of the civil aircraft according to claim 7, further comprising an audible and visual alarm component (6), wherein the audible and visual alarm component (6) is arranged on the outer side of the shell (5), and the film pressure sensor (24) is in communication connection with the audible and visual alarm component (6).

9. The automatic throttle on-off limiting device of civil aircraft according to claim 8, wherein the audible and visual alarm component (6) comprises a buzzer, a display lamp, a battery component and a throttle lever thrust value judging module, the battery component is respectively and electrically connected with the buzzer, the display lamp and the throttle lever thrust value judging module to provide electric energy, and the film pressure sensor (24), the buzzer and the display lamp are respectively and communicatively connected with the throttle lever thrust value judging module.

10. The automatic throttle on-off limiting device of civil aircraft according to claim 7, characterized in that the housing (5) is detachably connected with the wall plate (1).

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