CN217554170U - Limiting device of airplane manual control system - Google Patents
Limiting device of airplane manual control system Download PDFInfo
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- CN217554170U CN217554170U CN202220679062.XU CN202220679062U CN217554170U CN 217554170 U CN217554170 U CN 217554170U CN 202220679062 U CN202220679062 U CN 202220679062U CN 217554170 U CN217554170 U CN 217554170U
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Abstract
The utility model provides an aircraft manual control system stop device, include: the device comprises a drum wheel assembly, 2 input steel cables, 2 limiting blocks and 2 stop blocks; the drum wheel assembly comprises an inner sleeve and an outer sleeve sleeved outside the inner sleeve, an annular cavity is formed between the inner sleeve and the outer sleeve, and 2 through holes are formed in the outer sleeve; 2 stop blocks are arranged on the outer side of the outer sleeve, and each stop block is provided with a through hole; 2 input steel cables are wound on the inner sleeve in opposite winding directions and led out through the outer sleeve and the through holes corresponding to the stop blocks, and the part of each input steel cable outside the stop blocks is connected with 1 limiting block in a socket joint mode. The utility model discloses technical scheme has solved elevator trimmer control system's mechanical control mode, and the pilot is difficult to clearly and definitely perceive the amplitude of deflection of the elevator trimmer of the remote cable wire manipulation to lead to influencing the problem that normal flight was controlled.
Description
Technical Field
The utility model relates to a but not limited to aircraft control system's adjustment control technical field relates to an aircraft manual control system stop device.
Background
The elevator trim tab steering system belongs to an auxiliary steering system, and the trim tab is directly controlled by a driver. When the pilot wishes to maintain the main control surface at a given deflection position, the trim tab is deflected to generate a moment which corresponds to the movement of the main control surface, a compensation moment is generated to counteract the moment balance of the main control surface, and the pilot's steering moment is reduced, thereby reducing the pilot's physical effort and making the aircraft easier to steer.
Current elevator tab steering systems are of both electrically and mechanically operated type, which can steer the elevator tab to deflect. The existing mechanical operation is a steel cable type structure and is operated by an operation panel arranged in a cockpit; when a driver performs mechanical operation, the requirement that the elevator adjusting sheet deflects to an extreme position is met, because a steel cable in an operation system is long, an operation panel of the elevator adjusting sheet is usually arranged on a central operation platform, the stroke of the steel cable is completely generated by operation movement of the operation panel, in addition, the steel cable is wound on a rotating shaft of the operation panel, the rotating circle number of the rotating shaft is determined by the stroke of the steel cable, and because the diameter of the rotating shaft is not too large, the rotating circle number of the rotating shaft usually exceeds one circle.
The problem with the above-described mechanical manipulation of the current elevator tab manipulation system is that: it is difficult for the pilot to unambiguously perceive the magnitude of the deflection of the remote wire rope operated elevator tab, even affecting normal flight manoeuvres, by simply turning the steering wheel. Therefore, it is desirable to provide an embodiment that can tightly control the deflection of the aircraft trim tab to the extreme positions.
SUMMERY OF THE UTILITY MODEL
The purpose of the utility model is that: the utility model provides an aircraft manual control system stop device to solve elevator trimmer control system's mechanical control mode, the pilot is difficult to clearly and definitely the range of deflecting of the elevator trimmer of the remote cable wire manipulation of perception only through rotating the steering wheel, thereby leads to influencing the problem that normal flight was controlled.
The technical scheme of the utility model is that: the embodiment of the utility model provides an aircraft manual control system stop device, include: the drum wheel component 1, 2 input steel cables 2, 2 limiting blocks 6 and 2 stop blocks;
the drum wheel assembly 1 is of a cylindrical sleeve structure and comprises an inner sleeve and an outer sleeve sleeved outside the inner sleeve, an annular cavity is formed between the inner sleeve and the outer sleeve, and 2 through holes are formed in the outer sleeve; the 2 stop blocks are arranged on the outer side of the outer sleeve, and each stop block is provided with a through hole;
the 2 input steel cables 2 are wound on the inner sleeve in opposite winding directions and are led out through the outer sleeve and the through holes of the corresponding stop blocks, and the part of each input steel cable 2, which is positioned outside the stop block, is in socket joint with 1 limiting block 6.
Alternatively, in the aircraft manual control system limiting device as described above,
every stopper 6 includes the briquetting of two symmetry installations, and the middle part of two briquetting butt joints is provided with semicircular groove, and is provided with two screw holes that the position is the same for place cable wire 2 in the whole body slotted hole that forms after two briquetting docks, and pass the screw hole that two briquetting correspond the position through the screw, 1 input cable wire 2 among them of fixed connection.
Alternatively, in the aircraft manual operation system limiting device as described above,
the depth of the semicircular groove is smaller than the radius of the input steel cable 2, so that static friction force is formed between each limiting block 6 and the corresponding connected steel cable 2.
Alternatively, in the aircraft manual control system limiting device as described above,
the 2 stoppers comprise an upper stopper 7 and a lower stopper 8, the upper stopper 7 and the lower stopper 8 are respectively and fixedly installed at the top and the bottom of the outer sleeve in the drum wheel assembly 1, the installation surfaces of the upper stopper 7 and the lower stopper 8 are consistent with the outer surface of the outer sleeve corresponding to the installation positions, and one side end surface of each stopper used for limiting the corresponding limiting block 6 is vertical to the axis of the input steel cable 2.
Alternatively, in the aircraft manual control system limiting device as described above,
the position of the limiting block 6 in socket connection on the input steel cable 2 is determined according to the movement stroke of the input steel cable 2, and the maximum movement stroke of the input steel cable 2 is adjusted by adjusting the position of the limiting block 6.
Alternatively, in the aircraft manual operation system limiting device as described above,
the limiting device of the airplane manual control system is used for driving the input steel cables 2 to move through rotation of a control panel, wherein 1 input steel cable 2 is pulled out outwards, the other input steel cable 2 follows the inside of the drum wheel assembly 1, and the limiting device controls the maximum movement stroke of the input steel cable 2 which is pulled out outwards through limiting action of a limiting block 6 on the follow-up input steel cable 2 and a corresponding limiting block.
Alternatively, in the aircraft manual control system limiting device as described above,
the maximum movement stroke of the input steel cable 2 in the limiting device of the airplane manual control system which is pulled outwards is the sum of the lengths of the steel cables between the two limiting blocks 6 and the corresponding stop blocks.
The utility model has the advantages that: the embodiment of the utility model provides an aircraft manual control system stop device places 2 input cable wires with the winding of opposite winding direction in the inside sleeve that forms the ring cavity with outside sleeve by drum subassembly 1, and 2 input cable wires are drawn forth from the through-hole department of corresponding position on the outside sleeve respectively, and input cable wire 2 is located the outer part socket joint of dog and is connected with stopper 6. In addition, the position of a limiting block 6 connected with the input steel cable 2 in a socket mode is determined according to the movement stroke of the input steel cable 2, and the maximum movement stroke of the input steel cable 2 is adjusted by adjusting the position of the limiting block 6; the maximum movement path of the outgoing feed cable 2 can thus be controlled in the manner described above when the cable is moved by the operating panel. It can be seen that adopt the utility model discloses stop device obtains effectual trimmer declination control through simple adjustment, has reduced the system, shortens the lead-in period, moreover reliable accurate the limit declination of having guaranteed the trimmer.
The embodiment of the utility model provides a stop device sets up stop gear through the soft cable wire system at aircraft trimmer operating system, through simple adjustment, makes its reliable accurate through trimmer operating system with the trimmer restriction at the regulation angle, practiced thrift the cost. Furthermore, the limiting device is simple in structure, simple and reliable in adjustment mode, good in reaction effect and good in use prospect, and the system state is easy to guarantee.
Drawings
The accompanying drawings are included to provide a further understanding of the embodiments of the present invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the embodiments of the invention and not to limit the embodiments of the invention.
Fig. 1 is a schematic structural view of a limiting device of an aircraft manual control system provided by the present invention;
FIG. 2 is a schematic view of an application scenario of a limiting device of the aircraft manual control system provided in the embodiment shown in FIG. 1;
fig. 3 is a schematic structural view of a limiting block in the limiting device of the manual airplane control system according to the embodiment of the present invention;
fig. 4 is a schematic structural view of an upper stop block in a limiting device of a manual control system of an aircraft according to an embodiment of the present invention;
fig. 5 is a schematic structural view of a lower stop block in a limiting device of a manual control system of an aircraft according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The above background art has described a mechanical operating structure and operating mode of an elevator tab operating system, in which a wire rope is moved and a stroke thereof is generated by synchronous rotation of an operating wheel and a rotating shaft, however, since the diameter of the rotating shaft wound by the wire rope is generally small, the number of turns of the operating wire rope usually exceeds one turn, so that it is difficult for a pilot to clearly sense the deflection amplitude of an elevator tab operated by a remote wire rope by only rotating the operating wheel, and even normal flight operation is affected. That is, it is difficult to strictly control the deflection of the tab of the aircraft to the extreme position in the conventional mechanical manipulation manner, and thus it is important to strictly control the tab deflection angle of the aircraft.
The embodiment of the utility model provides a problem to current aircraft trimmer declination extreme position restriction, the embodiment provides an aircraft manual control system stop device can realize effectual control surface extreme position's control.
The present invention provides that several specific embodiments below can be combined with each other, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is the utility model provides a pair of aircraft manual control system stop device's structural schematic diagram, fig. 2 is the application scene sketch map of aircraft manual control system stop device that the embodiment shown in fig. 1 provided. The embodiment of the utility model provides an aircraft manual control system stop device includes: drum wheel components 1, 2 input steel cables 2, 2 limiting blocks 6, 2 stop blocks.
As shown in fig. 1 and fig. 2, in the limiting device of the aircraft manual control system, the drum wheel assembly 1 is provided with a cylindrical sleeve structure, and comprises an inner sleeve and an outer sleeve sleeved outside the inner sleeve, an annular cavity is formed between the inner sleeve and the outer sleeve, and the outer sleeve is provided with 2 through holes; the 2 stoppers are arranged on the outer side of the outer sleeve, and each stopper is provided with a through hole.
The embodiment of the utility model provides an in 2 input cable wires 2 with opposite winding direction twine on inside sleeve to draw forth, every through-hole through outside sleeve and corresponding dog input cable wire 2 is located the outer partial socket joint of dog and is connected with 1 stopper 6.
In practice, the input steel cord 2 is usually a flexible steel cord.
Fig. 3 is the embodiment of the utility model provides a structural schematic of stopper in the aircraft manual control system stop device. Every stopper 6 includes the briquetting of two symmetry installations, and the middle part of two briquetting butt joints is provided with semicircular groove, and is provided with two screw holes that the position is the same for place cable wire 2 in the whole body slotted hole that forms after two briquetting docks, and pass the screw hole that two briquetting correspond the position through the screw, 1 input cable wire 2 among them of fixed connection.
In practical application, the depth of the semicircular groove is smaller than the radius of the input steel cable 2, so that a static friction force is formed between each limiting block 6 and the corresponding steel cable 2 connected with the limiting block.
Fig. 4 is the structural schematic diagram of the upper stop block in the limiting device of the aircraft manual control system provided by the embodiment of the utility model, fig. 5 is the structural schematic diagram of the lower stop block in the limiting device of the aircraft manual control system provided by the embodiment of the utility model.
Referring to fig. 1, 4 and 5, in the embodiment of the present invention, each of the 2 stoppers includes an upper stopper 7 and a lower stopper 8, the upper stopper 7 and the lower stopper 8 are respectively and fixedly mounted on the top and the bottom of the outer sleeve in the drum assembly 1, the mounting surfaces of the upper stopper 7 and the lower stopper 8 are consistent with the outer surface of the outer sleeve corresponding to the mounting position, and a side end surface of each stopper for limiting the corresponding stopper 6 is perpendicular to the axis of the input cable 2.
It should be noted that, in the embodiment of the present invention, the specific position of the limiting block 6 in socket connection on the input steel cable 2 is determined according to the movement stroke of the input steel cable 2; in addition, the maximum motion stroke of the input steel rope 2 can be adjusted by adjusting the position of the limiting block 6.
Based on above-mentioned aircraft manual control system stop device's hardware structure, the embodiment of the utility model provides an in stop device's spacing principle does: when the input steel cables 2 are driven to move by the rotation of the control panel, 1 of the input steel cables 2 is pulled out, the other input steel cable 2 follows the inside of the drum wheel assembly 1, and the maximum movement stroke of pulling out the input steel cable 2 is controlled by the limiting action of the limiting blocks 6 on the following input steel cable 2 and the corresponding limiting blocks.
The embodiment of the utility model provides an in, the biggest motion stroke that input cable wire 2 outwards pulled out among the aircraft manual control system stop device is two stoppers 6 and corresponds cable wire length sum between the dog.
The embodiment of the utility model provides an aircraft manual control system stop device places 2 input cable wires with opposite winding direction winding in the inside sleeve of drum subassembly 1 and the annular cavity that outside sleeve formed, and 2 input cable wires are drawn forth from the through-hole department of corresponding position on the outside sleeve respectively, and input cable wire 2 is located the outer partial socket joint of dog and is connected with stopper 6. In addition, the position of a limiting block 6 connected with the input steel cable 2 in a socket mode is determined according to the movement stroke of the input steel cable 2, and the maximum movement stroke of the input steel cable 2 is adjusted by adjusting the position of the limiting block 6; thus, when the cable is moved by the operating panel, the maximum movement distance of the outgoing feed cable 2 can be controlled in the above-described adjustment manner. It can be seen, adopt the utility model discloses stop device obtains effectual trimmer declination control through simple adjustment, has simplified the system, shortens the development cycle, moreover reliable accurate the extreme declination of having guaranteed the trimmer.
The embodiment of the utility model provides a stop device sets up stop gear through the soft cable wire system at aircraft trimmer operating system, through simple adjustment, makes its reliable accurate through trimmer operating system with the trimmer restriction at the regulation angle, practiced thrift the cost. Furthermore, the limiting device is simple in structure, simple and reliable in adjustment mode, good in reaction effect and good in use prospect, and the system state is easy to guarantee.
The following describes a specific implementation of the limiting device of the manual airplane control system according to an embodiment of the present invention.
As shown in fig. 1 and fig. 2, the limiting device of the manual airplane control system provided by the embodiment of the present invention includes a moving component (2 input steel cables 2), a fixed base (drum assembly 1), a limiting block 6 and a stop block (including an upper stop block and a lower stop block). The input steel cable 2 can move along the vertical direction of the axis of the drum wheel assembly 1, the stop block is installed on the drum wheel assembly 1, and the limit block is installed on the input steel cable 2, so that the input steel cable 2 is finally accurately limited after moving to a specified position.
In the concrete implementation, the drum wheel assembly 1 is provided with a connecting part for mounting a stop block; in addition, the connection mode of the limiting block 6 and the corresponding input steel cable 2 is set as socket connection.
When the adjusting sheet control system is adjusted, the limiting block in the limiting device can be adjusted to a position far away from the stop block. Since the free angle of the tab is much greater than the design value, the neutral of the flight control system is adjusted first, and then the positive and negative declination angles of the tab are adjusted.
When the cockpit command piece, all links of the system and the control surface are adjusted to one-to-one corresponding positions (including a neutral position, an upper limit position and a lower limit position), the distance between the limiting block and the stop block is adjusted, so that after the deflection angle of the control surface reaches the limit deflection angle, the limiting block is contacted with the stop block, the limiting block is fixed at the position of the limit deflection angle and is prevented from loosening, and the limit deflection angle of the adjusting piece is reliably limited within a specified value. As shown in fig. 2, it is an application scenario schematic diagram of a limiting device of an aircraft manual control system provided by an embodiment of the present invention. Fig. 2 illustrates a specific position of the limiting device applied to the elevator tab control system, the integral limiting device is located at the front end of the guide plate 3, and the rear end of the guide plate 3 controls the control surface 4 through the drum 5 connected with the input steel cable 2; fig. 2 shows a specific state of the stopper device in the neutral position a, the upward limit position b, and the downward limit position c.
When the limiting mechanism of the airplane control system is designed, a limiting device is designed in a determined transmission link of the control system according to system analysis and unified coordination. The following description is given to the use mode of the limiting device of the aircraft manual control system in the embodiment of the present invention, and the steps include:
the first step is as follows: the operating system cable wire is used as a proper limit setting point.
The second step is that: the groove of the limiting block is designed according to the diameter of the steel cable, and the depth of the groove is smaller than the radius of the steel cable, so that larger static friction force between the limiting block and the steel cable is obtained.
The third step: the two limit blocks are fixed on the steel cable in a screw connection mode and are subjected to thread anti-loosening treatment.
The fourth step: designing a stop block according to the shape of the fixed base, wherein one side of the stop block for limiting is vertical to the axis of the steel cable; and the stop block is fixedly connected on the fixed support.
The fifth step: one surface of the stop block is parallel to one surface of the limiting block, which is vertical to the axis of the steel cable.
The eighth step: the limiting block and the fixing piece are provided with openings for the steel cable to pass through.
The ninth step: one end of the steel cable provided with the limiting block penetrates through the limiting block and the fixing part provided with the limiting block.
The tenth step: the cable wire extends through the tab handling system.
The eleventh step: the limiting block moves along with the steel cable line system, the distance between the stop block and the limiting block is determined according to the movement stroke of the steel cable, and the position of the limiting block is adjusted to limit the stroke of the operating system so as to achieve the purpose of limiting the operating surface.
In the present embodiment, taking the elevator tab control system as an example, according to the motion diagram of the control system (see fig. 2), a suitable set point is selected on the input steel cable 2; from the diagram of the movement of the tab manipulating system, the left and right limits of the movement of the moving part (i.e. the input steel cable 2) and its neutral position (see positions a, b and c in fig. 2) can be seen, thereby determining the movement stroke of the moving part steel cable at the set point.
The connecting threaded hole of the stop block is designed on the fixed support (namely the drum wheel component 1), the stop block is installed on the drum wheel component 1, the limit block 6 is installed on the steel cable, the distance between the limit block 6 and the stop block is adjusted, and after the input steel cable 2 moves to a certain stroke, the limit block 6 is reliably contacted with the stop block, so that the movement limit of the adjusting sheet control system is determined, and the deflection angle of the adjusting sheet 4 is limited.
Fig. 2 is a schematic view of a limiting mechanism, fig. 3 is a schematic view of a limiting block mechanism, fig. 4 is a schematic view of an upper stop structure, and fig. 5 is a schematic view of a lower stop structure. Wherein, the fixing support is arranged on the airplane structure and fixed by bolts.
Stopper 6 moves along with input cable 2, and two briquettings of stopper 6 link firmly through the screw, reach the adjustable purpose, and carry out locking processing after spacing nail and fan-shaped wheel spiro union, the dog rigid coupling is on drum subassembly 1 to in the region of cable wire motion, make the stopper reliably contact with the dog, thereby guarantee that the system is reliable spacing the spacing of reaching the trimmer.
Additionally, the utility model discloses there is the interior design of aircraft control system of input cable wire, work load when can effectively reducing the system adjustment. The utility model provides a shortcoming that system adjustment is complicated, the cycle length, simplify system adjustment process, shorten system adjustment cycle, guarantee operating system's adjustment state moreover. The effective deflection angle control of the adjustment sheet is obtained through simple adjustment, the system is simplified, the development period is shortened, and the limit deflection angle of the adjustment sheet is reliably and accurately ensured.
The utility model discloses aircraft control system stop device has verified on the key model aircraft of a certain series, through relevant department's reaction, and system stop device simplifies, and the adjustment is simple reliable, the system state also easily guarantees, and reaction effect is good, has fine use prospect.
Although the embodiments of the present invention have been described above, the description is only for the convenience of understanding the present invention, and the present invention is not limited thereto. The present invention is not limited to the above embodiments, but may be modified in various forms and details without departing from the spirit and scope of the present invention.
Claims (7)
1. A stop device for a manual control system of an aircraft, comprising: the drum wheel assembly (1), 2 input steel cables (2), 2 limiting blocks (6) and 2 stop blocks;
the drum wheel assembly (1) is of a cylindrical sleeve structure and comprises an inner sleeve and an outer sleeve sleeved outside the inner sleeve, an annular cavity is formed between the inner sleeve and the outer sleeve, and 2 through holes are formed in the outer sleeve; the 2 stop blocks are arranged on the outer side of the outer sleeve, and each stop block is provided with a through hole;
the 2 input steel cables (2) are wound on the inner sleeve in opposite winding directions and led out through the outer sleeve and the through holes of the corresponding stop blocks, and the part, outside the stop blocks, of each input steel cable (2) is connected with 1 limiting block (6) in a socket and spigot manner.
2. An aircraft manual handling system stop device according to claim 1,
every stopper (6) are including the briquetting of two symmetry installations, and the middle part of two briquetting butt joint faces is provided with semicircular groove, and is provided with two screw holes that the position is the same for place cable wire (2) in the whole body slotted hole that forms after two briquetting docks, and pass the screw hole that two briquetting correspond the position through the screw, 1 input cable wire (2) among them of fixed connection.
3. An aircraft manual handling system limiting device according to claim 2,
the depth of the semicircular groove is smaller than the radius of the input steel cable (2), so that static friction force is formed between each limiting block (6) and the corresponding steel cable (2) connected with the limiting block.
4. An aircraft manual handling system stop device according to claim 1,
each of the 2 stop blocks comprises an upper stop block (7) and a lower stop block (8), the upper stop block (7) and the lower stop block (8) are fixedly installed at the top and the bottom of the outer sleeve in the drum wheel assembly (1) respectively, the installation surfaces of the upper stop block (7) and the lower stop block (8) are consistent with the outer surface of the outer sleeve corresponding to the installation position, and one side end face of each stop block, which is used for limiting the corresponding limit block (6), is perpendicular to the axis of the input steel cable (2).
5. An aircraft manual operation system limiting device according to any one of claims 1 to 4,
the position of a limiting block (6) connected with the input steel cable (2) in a socket and spigot mode is determined according to the movement stroke of the input steel cable (2), and the maximum movement stroke of the input steel cable (2) is adjusted by adjusting the position of the limiting block (6).
6. An aircraft manual handling system limiting device according to any one of claims 1 to 4,
the limiting device of the airplane manual control system is used for driving the input steel cables (2) to move through rotation of a control panel, wherein 1 input steel cable (2) is pulled out outwards, the other input steel cable (2) follows the inside of the drum wheel assembly (1), and the limiting action of limiting blocks (6) on the follow-up input steel cables (2) and corresponding limiting blocks is used for controlling the maximum movement stroke of the input steel cables (2) which are pulled out outwards.
7. An aircraft manual handling system stop device according to claim 6,
the maximum movement stroke of the input steel cable (2) in the limiting device of the airplane manual control system, which is pulled outwards, is the sum of the lengths of the steel cables between the two limiting blocks (6) and the corresponding stop blocks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220679062.XU CN217554170U (en) | 2022-03-25 | 2022-03-25 | Limiting device of airplane manual control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220679062.XU CN217554170U (en) | 2022-03-25 | 2022-03-25 | Limiting device of airplane manual control system |
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| Publication Number | Publication Date |
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| CN217554170U true CN217554170U (en) | 2022-10-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220679062.XU Active CN217554170U (en) | 2022-03-25 | 2022-03-25 | Limiting device of airplane manual control system |
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| Country | Link |
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| CN (1) | CN217554170U (en) |
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