CN113819813A - Rudder feedback mechanism suitable for annular narrow space - Google Patents
Rudder feedback mechanism suitable for annular narrow space Download PDFInfo
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- CN113819813A CN113819813A CN202110968523.5A CN202110968523A CN113819813A CN 113819813 A CN113819813 A CN 113819813A CN 202110968523 A CN202110968523 A CN 202110968523A CN 113819813 A CN113819813 A CN 113819813A
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- 230000008713 feedback mechanism Effects 0.000 title claims abstract description 41
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 29
- 239000010959 steel Substances 0.000 claims abstract description 29
- 230000007246 mechanism Effects 0.000 claims abstract description 23
- 230000005540 biological transmission Effects 0.000 claims abstract description 11
- 230000006698 induction Effects 0.000 claims abstract description 7
- 238000013016 damping Methods 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 4
- 238000002955 isolation Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract description 14
- 238000013461 design Methods 0.000 abstract description 8
- 238000005259 measurement Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 12
- 238000010008 shearing Methods 0.000 description 9
- 230000009471 action Effects 0.000 description 8
- 230000010354 integration Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 238000001514 detection method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 125000004122 cyclic group Chemical group 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 230000007774 longterm Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000005381 potential energy Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000007306 functionalization reaction Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
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- 230000002093 peripheral effect Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
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- Mechanical Control Devices (AREA)
Abstract
The invention discloses a rudder feedback mechanism suitable for an annular narrow space, and relates to the technical field of weaponry. The device comprises a shell, a rear cover plate, a potentiometer assembly, magnetic steel, a rudder shaft and a shifting fork; the rear cover plate is installed on the shell, the steering shaft is installed on the shell and the rear cover plate in a rotating mode, the shifting fork is installed on the steering shaft and is in transmission connection with the transmission mechanism, the potentiometer assembly is installed on the rear cover plate, the magnetic steel is installed in the installation hole in the tail end of the steering shaft, and the center of the magnetic steel is opposite to the central induction area of the potentiometer assembly. The rudder feedback mechanism suitable for the annular narrow space adopts an integrated design, reduces the volume of occupying the steering engine cabin body, directly detects the rudder shaft, reduces interference factors, improves the measurement precision and reliability of products, has the characteristics of few parts, convenience in assembly and adjustment and low cost, and has very high practicability.
Description
Technical Field
The invention relates to the technical field of weapon equipment, in particular to a rudder feedback mechanism suitable for an annular narrow space.
Background
The steering engine is used as an important component of a missile control and guidance system actuating mechanism, and the performance directly determines the dynamic quality of a missile in the flight process.
The traditional rudder feedback mechanism has the disadvantages of complex structure, more parts, low integration level and complex assembly, and the installation needs to occupy a large volume of a steering engine cabin body, so that the rudder feedback mechanism is not suitable for installation in a narrow space. And, because of the high complexity of the traditional rudder feedback mechanism, the feedback precision no longer meets the design performance index requirements of the electric steering engine. A new rudder feedback mechanism with high integration, small number of parts and low assembly complexity is urgently needed to solve the problems.
Disclosure of Invention
The invention aims to provide a rudder feedback mechanism suitable for an annular narrow space, which is used for solving the technical problems of complex structure, more parts, large volume, low integration level, complex assembly and low feedback precision of the traditional rudder feedback mechanism.
In order to achieve the above purpose, the invention provides the following technical scheme:
there is provided a rudder feedback mechanism adapted for use in an annular narrow space, comprising: the device comprises a shell, a rear cover plate, a potentiometer assembly, magnetic steel, a rudder shaft and a shifting fork;
the utility model discloses a rear cover plate, including the housing, back shroud, steering column, shift fork, potentiometre subassembly, magnet steel, back shroud install on the housing, the steering column rotary type is installed the housing with on the back shroud, the shift fork is installed on the steering column to be connected with the drive mechanism transmission, the potentiometre subassembly is installed on the back shroud, the magnet steel is installed in the mounting hole of steering column tail end, the center of magnet steel with the central induction zone of potentiometre subassembly is relative.
Compared with the prior art, the rudder feedback mechanism suitable for the annular narrow space is designed according to the annular narrow space of the steering engine, the non-contact sensor is adopted, the interval with proper magnetic field intensity is reserved between the potentiometer component and the magnetic steel, in order to improve the inspection precision, the center of the magnetic steel is right opposite to the central induction area of the potentiometer component during the installation, the shell and the rear cover plate of the potentiometer component are directly used as a part of the outer shell of the steering engine according to the design of the annular space, the integration of structural function is realized, the volume occupied by the cabin body of the steering engine is reduced, the space utilization rate of the cabin body of the steering engine is improved, the rudder shaft is directly detected, other interference factors are greatly reduced, the measurement precision and the reliability of a product are greatly improved, and the rudder feedback mechanism has the advantages of fewer parts, convenience in assembly and adjustment, low cost and the like, has high practicability.
The invention also discloses a flight device, which comprises a steering engine and the rudder feedback mechanism in the first embodiment, wherein the steering engine is arranged in the flight device, and the rudder feedback mechanism is arranged in the rudder machine.
The beneficial effects of the flying device in the invention are the same as the technical effects of the rudder feedback mechanism suitable for the annular narrow space, and the technical effects are not repeatedly discussed here.
Drawings
The accompanying drawings, which are included to provide a further understanding of the 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 invention and not to limit the invention. In the drawings:
fig. 1 is a schematic view of a rudder feedback mechanism suitable for use in an annular narrow space in an embodiment of the present invention.
Reference numerals:
the device comprises a shell 1, a back cover plate 2, a potentiometer shell 3, a sensor 4, magnetic steel 5, a potentiometer cover plate 6, a damping ring 7, a first bearing 8, a shifting fork 9, a fixing pin 10, a second bearing 11, a rudder shaft 12 and a nut 13.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects to be solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.
Furthermore, the terms "first", "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise. The meaning of "a plurality" is one or more unless specifically limited otherwise.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
In the description of the present invention, it should be noted that unless otherwise explicitly stated or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those of ordinary skill in the art according to specific situations.
The first embodiment is as follows:
referring to fig. 1, a rudder feedback mechanism suitable for a narrow annular space according to an embodiment of the present invention includes: the device comprises a shell 1, a rear cover plate 2, a potentiometer assembly, magnetic steel 5, a rudder shaft 12 and a shifting fork 9;
the rear cover plate 2 is installed on the shell body 1, the rudder shaft 12 is rotatably installed on the shell body 1 and the rear cover plate 2, the shifting fork 9 is installed on the rudder shaft 12 and is in transmission connection with the transmission mechanism, the potentiometer component is installed on the rear cover plate 2, the magnetic steel 5 is installed in the installation hole at the tail end of the rudder shaft 12, and the center of the magnetic steel 5 is opposite to the center induction area of the potentiometer component.
In the specific implementation:
the rudder feedback mechanism adopts a non-contact sensor 4, an interval of proper magnetic field intensity is reserved between the sensor 4 and the magnetic steel 5, in order to improve the inspection precision, the center of the magnetic steel 5 faces a chip center sensing area of the sensor 4 as far as possible during installation, when the transmission mechanism drives the shifting fork 9 to move, the shifting fork 9 is fixed on the rudder shaft 12, the rudder shaft 12 rotates along the axial direction according to the transmission direction, the magnetic steel 5 is further driven to rotate, the sensor 4 detects the change of the magnetic field and carries out signal processing, the angle position of the rudder shaft 12 is calculated and a feedback signal is output, and therefore the feedback control of the rudder deflection angle is realized.
The rudder feedback mechanism suitable for the annular narrow space is designed according to the annular narrow space of the steering engine, a non-contact sensor is adopted, an interval with proper magnetic field intensity is reserved between a potentiometer assembly and the magnetic steel, in order to improve the inspection precision, the center of the magnetic steel is directly opposite to the central induction area of the potentiometer assembly during installation, the shell and the rear cover of the potentiometer assembly are directly used as a part of the shell of the steering engine according to the design of annular space, the integration of structural functions is realized, the volume occupied by the steering engine cabin body is reduced, the space utilization rate of the steering engine cabin body is improved, the rudder shaft is directly detected, other interference factors are greatly reduced, and the measurement precision and the reliability of the product are greatly improved, meanwhile, the device has the advantages of few parts, convenience in assembly and adjustment, low cost and the like, and has high practicability.
As an embodiment, the potentiometer assembly includes a potentiometer housing 31, a sensor 4, and a potentiometer cover 6; the sensor 4 is installed in the installation groove of the potentiometer shell 31, the potentiometer cover plate 6 is buckled on the potentiometer shell 31, the sensor 4 is covered in the potentiometer shell 31, the potentiometer shell 31 is installed on the rear cover plate 2, and the potentiometer cover plate 6 faces the magnetic steel 5. Further, the potentiometer cover plate 6 is made of a magnetic isolation material.
The potentiometer shell 31 and the back cover plate 2 are designed according to the annular narrow space on the steering engine, and are directly used as a part of the outer shell body 1 of the steering engine after being designed, so that the structure and the function are integrated, the structure is more compact, and the potentiometer shell 31 and the potentiometer cover plate 6 realize the installation and fixation of the sensor 4. The potentiometer cover plate 6 made of magnetism isolating materials effectively reduces the interference of external signals and improves the accuracy of electromagnetic signal detection.
As an embodiment, the center of the magnetic steel 5 is directly opposite to the central sensing area of the sensor 4.
The sensor 4 is in a non-contact type, an interval with proper magnetic field intensity is reserved between the sensor 4 and the magnetic steel 5 during installation, and the center of the magnetic steel 5 is opposite to the central induction area of the sensor 4, so that the detection precision is further ensured.
As an embodiment, the rudder feedback mechanism further comprises a damping ring 7; the damping ring 7 is located at the aft end mounted on the rudder shaft 12.
The damping ring 7 is arranged, so that a good excitation effect can be achieved, furthermore, the damping ring 7 and the magnetic steel 5 are located in the same plane, the effect that the sensor 4 receives electromagnetic signals is ensured, and the accuracy of electromagnetic signal detection is further improved.
As an alternative, the side of the back cover 2 facing the potentiometer module is provided with an annular groove, in which the damping ring 7 is pressed by the potentiometer housing 31 and the potentiometer cover plate 6.
The annular groove is convenient for mounting and fixing the damping ring 7, and the potentiometer shell 31 and the potentiometer cover plate 6 are pressed, so that the rudder feedback mechanism is higher in integration level, more compact in structure and smaller in occupied space.
As an embodiment, the rudder feedback mechanism further comprises a first bearing 8 and a second bearing 11; the first bearing 8 is arranged on the rear cover plate 2, and the tail end of the rudder shaft 12 is rotatably arranged on the rear cover plate 2 through the first bearing 8; the second bearing 11 is mounted on the housing 1, and the rudder shaft 12 is rotatably mounted on the housing 1 via the second bearing 11. Further, the shift fork 9 is located between the first bearing 8 and the second bearing 11.
The tail end of the rudder shaft 12 is arranged on the rear cover plate 2 through the first bearing 8 and arranged on the shell 1 through the second bearing 11, so that the degree of freedom of the rudder shaft 12 in other directions is limited, the rudder shaft 12 can better rotate, the friction force in the rotating process of the rudder shaft 12 is reduced, the transmission output of the transmission mechanism can be better transmitted to the rudder shaft 12 through the shifting fork 9, and the detection effect of the sensor 4 is further improved. The shift fork 9 of setting between first bearing 8 and second bearing 11 when as the driving medium, also plays the effect of retaining ring to second bearing 11, realizes the multi-functionalization of part.
As an embodiment, the rudder feedback mechanism further includes a fixing pin 10 and a nut 13; the fork 9 is mounted on the rudder shaft 12 by means of a fixing pin 10 and a nut 13.
The shifting fork 9 adopts the installation form of the fixed pin 10 and the nut 13, so that the shifting fork 9 is more convenient to install, and the shifting fork 9 is more convenient to install, disassemble and maintain.
Example two:
the invention also discloses a flight device, which comprises a steering engine and the rudder feedback mechanism in the first embodiment, wherein the steering engine is arranged in the flight device, and the rudder feedback mechanism is arranged in the rudder machine.
The steering engine is used as an important component of a control and guidance system actuating mechanism of the flight device, and the performance directly determines the dynamic quality of the flight device in the flight process. In order to better improve the feedback precision of the steering engine of the flight device in the flight state, a rudder feedback mechanism is designed, and in order to better realize launching of the flight device, a mechanical type control surface folding and unfolding mechanism for the steering engine is also designed.
The mechanical control surface folding and unfolding mechanism for the steering engine comprises a shell, a first return spring, a connecting rod, a guide rod, equal number of control shafts, control surfaces and elastic return assemblies; the rudder shafts, the rudder surfaces and the elastic return assemblies are all multiple and are in one-to-one correspondence, the rudder shafts are uniformly arranged on the periphery of the shell, the rudder surfaces are hinged to one ends, far away from the shell, of the corresponding rudder shafts, a cavity is formed in the middle of each rudder shaft, and the elastic return assemblies are arranged in the cavities; the guide rod is vertically installed on the shell, the connecting rod is installed on the guide rod in a sliding mode, the starting end of the connecting rod is fixedly connected with the shell through a shearing pin, the first return spring is installed on the connecting rod and abuts against the shell and is in a compressed state, the tail end of the connecting rod is provided with a limiting column, the tail end of the control surface is provided with a positioning groove, and movable gaps for the connecting rod to move towards the shell when the connecting rod is overloaded and are preset among the connecting rod, the shell and the control surface; when the control surface is not unfolded, the elastic return component is abutted against the control surface and is in a compressed state, and the limiting column is inserted into the positioning groove; the shear pin is sheared by the overload of the connecting rod, the limiting column is separated from the positioning groove, and the control surface is unfolded under the action of the elastic restoring component.
In the specific implementation:
the rudder shaft is hinged with the rudder surface through a support pin; the second return spring and the unlocking pin are arranged in the cavity of the rudder shaft; the bottom plate is fixedly connected with the connecting rod through a shearing pin; the locking nut fixes the shear pin through the tail end thread of the shear pin; the first return spring is installed in the installation groove of the connecting rod in a compression mode; the bottom plate is fixed on the shell through screws, the guide rod penetrates through a through hole in the connecting rod and is screwed and installed on the shell through self tail end threads, and meanwhile, the freedom degrees of the connecting rod in other directions except the axial direction are limited. The connecting rod fixes the control surface through a positioning groove embedded in the tail end of the control surface. Furthermore, the number of the control surfaces and the number of the control shafts are respectively, and the control shafts are uniformly distributed on the peripheral side of the shell. The rudder shaft and rudder surface can also be other numbers, such as, for example, etc., which are locked and structurally stable when deployed.
The initial state of the control surface is folding locking, the control surface is designed to rotate around a supporting pin, the freedom degree of the control surface in other directions is limited through a control shaft notch and a connecting rod, and meanwhile, the opening lock pin is pushed to compress a second return spring to move in a mounting hole of the control shaft. The link is fixed to the base plate by a shear pin and compresses the first return spring in the axial direction. The bottom plate is further fixed on the shell to realize the fixation of the connecting rod, and the connecting rod is embedded into the tail end positioning groove of the control surface through the limiting column to effectively lock the control surface.
Unlocking and unfolding the control surface: the steering engine is subjected to axial downward overload acceleration when being launched, the connecting rod shears and locks the shearing pin moving under the action of the overload, and after the shearing pin is broken, the connecting rod continues to move downwards until the shell limits the shearing pin. When the overload of the steering engine disappears, the connecting rod moves upwards along the guide rod under the action of the elastic potential energy stored in the first return spring, after the limiting column of the connecting rod is separated from the positioning groove at the tail end of the control surface, the control surface is unlocked, and meanwhile, the first return spring continues to push the connecting rod to move upwards until the top end of the guide rod limits the connecting rod. After the control surface is unlocked, under the action of elastic potential energy stored in a shackle lock spring, the retractable pin is pushed to move forwards, a torque is formed to push the control surface to rotate by taking the support pin as a shaft, the control surface rotates along the needle to be unfolded, when the control surface is unfolded to a position, the control shaft limits the control surface to continue rotating clockwise, the unlocking pin abuts against a limiting boss on the control surface, and the limiting boss limits the retractable pin, so that unfolding and locking of the control surface are realized. As shown in the figure.
Compared with the prior art, in the mechanical control surface folding and unfolding mechanism provided by the invention, the control surface is hinged on the control shaft through the support pin and can rotate around the support pin, the control surface can be close to or separated from the support pin, the elastic return assembly in a compressed state can provide a restoring force for unfolding the control surface, the guide rod is arranged to enable the connecting rod to move along the guide rod without being separated from the shell, the connecting rod and the shell are fixed through the shear pin, the shear pin can be cut off when the connecting rod is overloaded, the first return spring is further compressed, the connecting rod can be far away from the shell under the action of the first return spring after the overload disappears and then is separated from the control surface, and the control surface after unlocking can be unfolded under the action of the elastic return device. Above-mentioned folding deployment mechanism of mechanical type rudder face adopts the structural design that integrates, compact structure, and occupation space is little, and is high to the space utilization of steering wheel, and deployment mechanism make full use of the overload force that shell transmission process produced carries out the unblock of mechanism, and the unblock function is reliable, has satisfied the muzzle and has realized the functional demand that the steering wheel opened the rudder, has solved the chronogenesis drawback that electrical command carries out the rudder face unblock, has very high practicality.
The invention also has the following effects:
a) the steering engine has the advantages that a miniaturized and integrated structural design technology is adopted, the four-rudder locking function is integrated, a simple mechanism is adopted for design, the structure is compact, the occupied space is small, and the space utilization rate of the steering engine is high;
b) the mechanism fully utilizes the overload force generated in the cannonball launching process to unlock the mechanism, has reliable unlocking function, can meet the functional requirement of opening the rudder of a steering engine at a cannon muzzle, and avoids the time sequence defect of unlocking the rudder surface by an electrical instruction;
c) the mechanism has the advantages of simple principle of locking and unfolding the control surface, compact structure, few parts, reliable mechanism, high overload resistance, low manufacturing cost and good economy, meets the requirement of guided projectiles on the structural strength of the mechanism, and promotes the low cost and integrated design of the steering engine;
d) the mechanism adopts a mechanical structure to realize the locking and the unfolding of the control surface, can carry out a plurality of tests and dismounting at the same time, does not influence the performance of the mechanism, does not need special maintenance, and can realize long-term storage under various severe environments.
As an embodiment, the elastic return assembly comprises a second return spring and an unlocking pin; the second is replied the spring and is installed in the cavity at rudder axle middle part, and the one end that the casing was kept away from to the unblanking pin is installed at the second and is replied the spring, and the unblanking pin is accomodate in the rudder axle and is offseted with the rudder face.
The second return spring is in a compressed state when the control surface is locked, elastic restoring force can be provided for unfolding of the control surface, the unlocking pin is arranged to replace the second return spring to be in contact with the control surface, and the contact effect of the unlocking pin and the control surface is guaranteed. Furthermore, one end, far away from the control surface, of the second return spring can be selected to be clamped in the control shaft, and the situation that the second return spring and the unlocking pin are disengaged from the control shaft after the control surface is unfolded is avoided.
As one possible embodiment, the control surface is provided with a limit boss, when the control surface is not unfolded, the unlocking pin is in positive contact with the limit boss, and after the control surface is unfolded, the unlocking pin is in contact with the side surface of the limit boss.
The arrangement of the limiting boss ensures the contact effect of the unlocking pin and the control surface when the control surface is not unfolded, and the limiting boss is abutted against the unlocking pin when the control surface is unfolded, so that the second return spring and the unlocking pin can be prevented from being separated from the control shaft, the control surface can be continuously supported, and the control surface is prevented from shaking.
As an implementation mode, the end of the rudder shaft far away from the shell is provided with a mounting platform, the rudder surface is hinged on the mounting platform, and the rudder surface is in a horizontal state after being unfolded. Furthermore, a fixed block is arranged on one side, far away from the limiting boss, of the control surface, and after the control surface is unfolded, the fixed block abuts against the mounting table.
The setting of mount table has made things convenient for the installation of rudder face fixed, the setting of fixed block on the rudder face for the rudder face is in the expansion back, and the fixed block offsets with the mount table, avoids the continuation of rudder face to rotate, and cooperation second is replied the spring and is unblanked the round pin, avoids rocking of rudder face.
As an embodiment, the housing further comprises a bottom plate; the bottom plate is fixedly installed on the shell, a through hole is formed in the middle of the bottom plate, the starting end of the connecting rod is inserted into the through hole and fixed through the shearing pin, and the connecting rod can move in the hole opening direction of the through hole when the connecting rod is not fixed.
The bottom plate passes through the mounting screw on the casing, and the middle part of bottom plate is provided with the through-hole that runs through from top to bottom, and the initiating terminal cartridge of connecting rod is in the through-hole to it is fixed through the shear pin, and the shear pin is fixed through lock nut, has guaranteed the fixed effect of shear pin to the connecting rod. When the connecting rod is overloaded, the connecting rod moves towards the shell, the shearing pin is sheared, the connecting rod continues to move towards the shell, the first return spring is compressed, and the starting end of the connecting rod is finally contacted with the shell to limit the connecting rod.
In one embodiment, an annular boss is disposed on the periphery of the bottom plate, and one end of the first return spring facing the housing abuts against the annular boss. Further, the shear pin is located on a side of the annular boss facing the housing.
The setting of cyclic annular boss, can provide fine support for first return spring, the direct contact of first return spring and casing has also been avoided, first return spring is located the one side that the casing was kept away from to cyclic annular boss on the bottom plate, will cut the opposite side that the round pin installed the cyclic annular boss on the bottom plate, there is not first return spring's interference, installation convenience more to the shearing round pin, adopt pure mechanical structure, can carry out many times test and dismouting, do not influence its performance, do not need special maintenance, can realize long-term storage under various adverse circumstances.
As an embodiment, the length of the guide rod is greater than the length of the connecting rod.
The setting of guide arm has played the effect of direction for the removal of connecting rod, and the length of guide rod is greater than the length of connecting rod, has ensured that the spacing post of connecting rod can deviate from in following the constant head tank on the rudder face, and the connecting rod moves along the guide arm, offsets with the end of guide arm at last, avoids deviating from of connecting rod.
The invention also provides a using method of the mechanical control surface folding and unfolding mechanism, which comprises the following steps:
when the lock is locked: rotating the control surface to a locking position, compressing the elastic restoring device by the control surface, pushing the connecting rod to move towards the direction of the shell until a limiting column arranged at the tail end of the connecting rod is inserted into a positioning groove corresponding to the tail end of the control surface, and fixing the starting end of the connecting rod on the shell by using a shear pin;
when unlocking: the connecting rod is overloaded and moves towards the shell, the connecting rod compresses the first return spring, the connecting rod shears the shearing pin, after the overload disappears, the connecting rod moves towards the direction far away from the shell under the action of the first return spring and is separated from the control surface, and the control surface is unfolded under the action of the elastic return device.
In the foregoing description of embodiments, the particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. A rudder feedback mechanism adapted for use in an annular narrow space, comprising: the device comprises a shell, a rear cover plate, a potentiometer assembly, magnetic steel, a rudder shaft and a shifting fork;
the utility model discloses a steering wheel, including rear cover, rudder axle, back shroud, shift fork, potentiometre subassembly, magnet steel, back shroud installs on the casing, the rudder axle rotary type is installed the casing with on the back shroud, the shift fork is installed on the rudder axle to be connected with the drive mechanism transmission, the potentiometre unit mount is in on the back shroud, the magnet steel is installed in the mounting hole of rudder axle tail end, the center of magnet steel with the center induction zone of potentiometre subassembly is relative.
2. A rudder feedback mechanism adapted for use in small annular spaces as in claim 1 wherein said potentiometer assembly includes a potentiometer housing, a sensor and a potentiometer cover plate;
the sensor is installed in the mounting groove of potentiometer shell, potentiometer cover plate lock joint is in on the potentiometer shell, will the sensor cover is established in the potentiometer shell, the potentiometer shell is installed on the back shroud, the orientation of potentiometer cover plate the magnet steel.
3. The rudder feedback mechanism suitable for the annular narrow space according to claim 2, wherein the center of the magnetic steel is directly opposite to the central sensing area of the sensor.
4. The rudder feedback mechanism for small annular spaces as claimed in claim 1, wherein the potentiometer cover plate is made of a magnetic isolation material.
5. A rudder feedback mechanism adapted for use in an annular narrow space as described in claim 1 wherein said rudder feedback mechanism further includes a damping ring;
the damping ring is arranged at the tail end of the rudder shaft.
6. A rudder feedback mechanism adapted for use in an annular narrow space as in claim 5 wherein the side of the back cover plate facing the potentiometer assembly is provided with an annular groove into which the damping ring is compressed by the potentiometer housing and the potentiometer cover plate.
7. A rudder feedback mechanism adapted for use in an annular narrow space as described in claim 1 wherein said rudder feedback mechanism further comprises a first bearing and a second bearing;
the first bearing is arranged on the rear cover plate, and the tail end of the rudder shaft is rotatably arranged on the rear cover plate through the first bearing; the second bearing is installed on the shell, and the rudder shaft is rotatably installed on the shell through the second bearing.
8. A rudder feedback mechanism adapted for use in small annular spaces as in claim 7 wherein said fork is located between said first bearing and said second bearing.
9. A rudder feedback mechanism adapted for use in an annular narrow space as in claim 1 further including a fixing pin and a nut;
the shifting fork is installed on the rudder shaft through the fixing pin and the nut.
10. A flying device based on the rudder feedback mechanism as claimed in any one of claims 1 to 9, further comprising a steering engine;
the steering engine is installed in the flying device, and the rudder feedback mechanism is installed in the rudder engine.
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| CN108286918A (en) * | 2017-12-29 | 2018-07-17 | 中国航天空气动力技术研究院 | A kind of how shaft-driven annular rudder control unit |
| CN110260777A (en) * | 2019-07-05 | 2019-09-20 | 贵州航天控制技术有限公司 | A kind of embedded rudder face corner measuring apparatus |
| CN110260728A (en) * | 2019-07-05 | 2019-09-20 | 贵州航天控制技术有限公司 | A kind of four rudder cluster type electric rudder systems |
| CN110455132A (en) * | 2019-08-30 | 2019-11-15 | 贵州航天控制技术有限公司 | A kind of small-sized integral type combination control mechanism |
| CN216348108U (en) * | 2021-08-23 | 2022-04-19 | 贵州航天控制技术有限公司 | Rudder feedback mechanism suitable for annular narrow space |
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2021
- 2021-08-23 CN CN202110968523.5A patent/CN113819813A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108286918A (en) * | 2017-12-29 | 2018-07-17 | 中国航天空气动力技术研究院 | A kind of how shaft-driven annular rudder control unit |
| CN110260777A (en) * | 2019-07-05 | 2019-09-20 | 贵州航天控制技术有限公司 | A kind of embedded rudder face corner measuring apparatus |
| CN110260728A (en) * | 2019-07-05 | 2019-09-20 | 贵州航天控制技术有限公司 | A kind of four rudder cluster type electric rudder systems |
| CN110455132A (en) * | 2019-08-30 | 2019-11-15 | 贵州航天控制技术有限公司 | A kind of small-sized integral type combination control mechanism |
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