CN212448036U - Rotating assembly and aircraft adopting same - Google Patents
Rotating assembly and aircraft adopting same Download PDFInfo
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- CN212448036U CN212448036U CN202020787332.XU CN202020787332U CN212448036U CN 212448036 U CN212448036 U CN 212448036U CN 202020787332 U CN202020787332 U CN 202020787332U CN 212448036 U CN212448036 U CN 212448036U
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Abstract
The utility model discloses a rotating assembly and adopt its aircraft, including the turned angle piece, for turned angle piece pivoted angle setting element and the articulated locking mechanism of action between locking position and unblock position, the interval is provided with at least one block portion on the turned angle piece in the rotation week, the angle setting element on be provided with block portion complex location portion, articulated locking mechanism keep location portion and block portion to be in the fit state when being in the locking position. The runner assembly simple structure, compactness, the stability of rotation is good, the precision is high to the locking rotating state that can be reliable, promptly, keep being in that the aircraft is stable and expand state, folded state and can not take place to shift, thereby guarantee flight stability and security, guarantee folded state's stability, the fail safe nature of guarantee runner assembly placing, transportation.
Description
Technical Field
The utility model relates to an aircraft technical field especially relates to a rotating assembly and adopt its aircraft.
Background
In the aircraft especially unmanned aerial vehicle field, can adopt foldable structure usually, expand the horn when needs fly, and then collapsible the drawing in when needs are accomodate, are transported, reduce occupation space, are convenient for deposit, improve space utilization, reduce cost of transportation. But the rotation folding mechanism who adopts at present often has the inaccurate situation of turned angle, uses the reliability low, is difficult to the stable expansion or the state of drawing in that keeps, appears folding mechanism's situation of aversion easily at flight or deposit the in-process to lead to the flight condition unstable the impaired situation of unmanned aerial vehicle that appears easily, also can lead to unmanned aerial vehicle unexpected when depositing to expand and be touched by mistake and lead to impaired situation.
SUMMERY OF THE UTILITY MODEL
The utility model discloses the technical problem that will solve and the technical task who provides improve prior art, provide a runner assembly, solve the rotation folding mechanism turned angle inaccuracy among the prior art, be difficult to keep expanding or the state of drawing in, appear shifting easily and lead to impaired problem.
For solving the above technical problem, the technical scheme of the utility model is that:
the utility model provides a rotating assembly, includes rotation angle spare, for rotation angle spare pivoted angle setting element and the articulated locking mechanism of action between locking position and unblock position, the interval is provided with at least one block portion on the rotation angle spare in the rotation week, the angle setting element on be provided with block portion complex location portion, articulated locking mechanism keep location portion and block portion to be in the fit state when being in the locking position. The rotating component of the utility model has the functions of angle positioning and locking, the rotating angle piece and the angle positioning piece are respectively connected with the parts which need to realize hinging, the rotating angle positioning is realized by matching the clamping part on the rotating angle piece with the positioning part on the angle positioning piece, namely, when the angle positioning piece and the rotating angle piece rotate relatively until the positioning part and the clamping part are matched, the rotating angle is in place, the accuracy of the rotating angle is ensured, the excessive rotation or insufficient rotation is avoided, and the current rotating angle state is kept by the hinged locking mechanism when the rotating angle is in place, namely, the stable unfolding state or folding state can be kept, the situation that the unfolding state is unstable in the flying process and the shaking or even the accidental folding is caused is avoided, and the dangerous situation that the flying state is unstable and the crash is caused is avoided, simultaneously also effectively ensure the stability of draw in the state in to the guarantee is placed or the stability of transportation, avoids appearing folding horn structure accident and expandes and lead to appearing colliding with impaired situation, ensures the fail safe nature that unmanned aerial vehicle placed, the transportation.
Further, block portion be the recess, location portion for with recess complex arch, adopt recess and protruding complex mode, simple structure, processing is realized conveniently, with low costs to recess and bellied cooperation can very accurate realization turned angle location, the rotation of guarantee every can both be accurate reach predetermined angular position, thereby can ensure the stability of the flight state after unmanned aerial vehicle expandes, also guarantee the compactness of draw in the state in, avoid unmanned aerial vehicle to draw in and have the deviation and take place to interfere with the extranal packing and lead to the situation of vanning transportation difficulty.
Furthermore, block portion set up on the ascending terminal surface that is close to the angle locating piece of the edge rotation axial of angle of rotation piece, location portion corresponding set up on the ascending terminal surface that is close to the angle of rotation piece of the edge rotation axial of angle locating piece, compact structure does not occupy the space that rotates circumference.
Furthermore, when the hinged locking mechanism is in the locking position, an acting force along the rotation axial direction is applied to enable the rotation angle piece and the angle positioning piece to be pressed tightly so as to keep the positioning part and the clamping part in a matching state, and the clamping part and the positioning part are kept in the matching state by adopting a mechanical pressing mode, so that the implementation is convenient and simple.
Furthermore, articulated locking mechanism include the locking piece of activity in perpendicular to axis of rotation upwards, the locking piece on be provided with the driving inclined plane that is used for compressing tightly rotation angle spare and angle setting element that inclines to rotation axial. Simple structure, the function of realization locking that can be reliable, it is convenient to implement, and is with low costs, the locking piece is when moving along perpendicular to rotation axial direction, drive inclined plane on the locking piece can produce along the ascending displacement volume of rotation axial (along the ascending effort of rotation axial), thereby can be compressed tightly angle of rotation spare and angle positioning element together along rotation axial, and then make inseparabler the inserting in the block portion of recess form in the location portion of protruding form, the clearance of dodging does not upwards be followed in the axis of rotation between angle of rotation spare and the angle positioning element this moment, thereby the unable block portion of following recess form in location portion of protruding form withdraws from, thereby unable relative rotation that takes place between angle of rotation spare and the angle positioning element, and then the current angle of rotation state of locking has been realized, namely, can keep stable expansion state or draw in state. When needs unblock, only need in perpendicular to rotate axial direction in the reverse movement locking piece can to remove turned angle piece and angle setting element and rotate the ascending state that compresses tightly of axial, and then can carry out relative rotation between turned angle piece and the angle setting element, promptly, unmanned aerial vehicle can be in the expansion and draw in the state between switch.
Furthermore, articulated locking mechanism still include path direction perpendicular to and rotate axial channel subassembly, the locking piece slide along channel subassembly route in order to switch between locking position and unblock position, ensure that the locking piece can be stable move about along perpendicular to rotation axial direction, also avoid the locking piece to take place along rotation axial's aversion simultaneously to the realization that ensures the reliable and stable of driving inclined plane of locking piece can compress tightly angle of rotation piece and angle setting element along the function that the rotation axial compresses tightly.
Furthermore, still include the pivot, one of them non-rotatable setting of turned angle spare and angle setting element in the pivot, the rotatable setting of another can improve the holistic structural stability of runner assembly in the pivot, improves turned angle spare and angle setting element stability of relatively rotating, avoids producing radial relative skew between turned angle spare and the angle setting element.
Furthermore, the elastic part is used for pre-pressing the rotation angle part and the angle positioning part along the rotation axial direction, the rotation angle part and the angle positioning part are elastically pressed by utilizing the elastic force generated by the elastic part, so that the rotation angle part and the angle positioning part can be elastically avoided in the rotation axial direction, and the positioning part and the clamping part can be tightly matched by the elastic force generated by the elastic part, so that the rotation angle positioning effect is stably played, and the rotation angle positioning function can be realized by avoiding the situation that the positioning part and the clamping part cannot be effectively matched due to the overlarge gap between the rotation angle part and the angle positioning part in the rotation axial direction.
Further, still include the nut, rotation angle piece, angle setting element, locking piece, elastic component and nut overlap in proper order and locate in the pivot, elastic component one end support and lean on the nut, the other end is applyed along rotating axial's effort to the locking piece. The nut is utilized to limit and assemble each part on the rotating shaft, so that each part is prevented from falling off, the stable performance of each function of each part is ensured, and the fixed position of the nut on the rotating shaft is adjustable, so that the compression amount of the elastic part is adjusted, the pre-compression force between the rotation angle part and the angle positioning part is adjusted, and the function of adjusting the rotation damping is realized.
The utility model provides an aircraft, adopts foretell runner assembly to constitute and rotates beta structure, can make the aircraft carry out accurate expansion or draw in to keep the steadiness of expansion state, draw in the state, avoid appearing shifting and lead to the state to change, improve flight stability and security.
Compared with the prior art, the utility model discloses the advantage lies in:
the runner assembly simple structure, compactness, the stability of rotation is good, the precision is high to the locking rotating state that can be reliable, promptly, keep being in that the aircraft is stable and expand state, folded state and can not take place to shift, thereby guarantee flight stability and security, guarantee folded state's stability, the fail safe nature of guarantee runner assembly placing, transportation.
Drawings
FIG. 1 is a structural schematic view of an aircraft in a deployed state;
FIG. 2 is a schematic structural view of the aircraft in a stowed condition;
FIG. 3 is a schematic view of the articulation of the main arm with the folding arm;
FIG. 4 is a schematic structural view of the main arm connected to the folding arm via the rotating assembly;
FIG. 5 is an exploded view of the rotating assembly;
FIG. 6 is a schematic structural view of the rotary shaft assembly according to the second embodiment;
fig. 7 is a schematic structural view of the rotary shaft assembly according to the third embodiment.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The embodiment of the utility model discloses a rotating assembly, the rotation precision is high, stable good, and the aversion appears in current gesture effectively avoiding locking expansion state and the state of drawing in that can be reliable, improves flight stability and security, avoids the aircraft impaired, ensures the integrity of aircraft.
Example one
As shown in fig. 1 to 5, an aircraft mainly includes a fuselage a, a horn assembly b and a rotor power assembly c, where the fuselage a includes a housing 1 formed by processing a plate-shaped material and having a receiving cavity therein, the housing 1 is provided with a cavity 11 having an inwardly recessed wall surface, the horn assembly b is hinged to the cavity 11 to form a folding horn structure, the rotor power assembly c is disposed on the horn assembly b, and the horn assembly b is further provided with a foldable undercarriage d;
the shell 1 and the horn component b are specifically formed by processing carbon fiber composite materials, the carbon fiber composite materials are excellent in mechanical property, small in specific gravity, good in rigidity and high in strength, and the specific strength and the specific modulus comprehensive index are high, so that the shell 1 and the horn component b are guaranteed to have excellent structural strength, the fuselage a and the horn component b are only thin shell-shaped structures, reinforcing ribs are not required to be arranged, the horn component b is directly connected to the shell 1, a structural framework is not required to be arranged in the fuselage, the waste weight of an aircraft is effectively reduced, the bearing capacity is improved, and the endurance time is prolonged;
the aircraft arm assembly b comprises a main arm b1 and a folding arm b2, wherein the main arm b1 and the folding arm b2 are both made of carbon fiber composite materials and have hollow cylindrical structures, the weight is light, the structural strength is high, a rotor power assembly c is arranged on the main arm b1, one end of the folding arm b2 is hinged with the main arm b1 through a rotating assembly 3, the other end of the folding arm b2 is hinged with a cavity groove 11 of a shell 1, in particular, the main arm b1 is in a quadrilateral long rod shape along the front-back direction of an aircraft body a, two folding arms b2 are arranged in parallel along the length direction of the main arm b1 at intervals to form a parallel folding aircraft arm structure, the structural stability in a unfolding state is good, the stability and the safety of flight are guaranteed, the rotor power assemblies c are respectively arranged at two ends of the main arm b1, the cavity grooves 11 for connecting the aircraft arm assembly b are symmetrically arranged at the left side and the right side of the aircraft body a, thereby the left and right sides symmetric connection at fuselage a has the horn subassembly b to constitute the aircraft of four rotors, folding arm rotate along the fore-and-aft direction of fuselage, the main arm then is keeping away from or being close to the side about the fuselage in the horizontal direction, for the expansion state when the fuselage left and right sides is kept away from to the main arm, for the folded state when the main arm is close to the fuselage left and right sides, the aircraft all is main arm length at the shared space length of fuselage fore-and-aft direction when expansion state and folded state, and because horn subassembly b folds along the fore-and-aft direction, thereby can not increase the occupation space of direction of height when folded state, can make the folded state compacter.
The rotating assembly 3 for connecting the folding arm b2 and the main arm b1 mainly comprises a rotating angle component 31, an angle positioning component 32 rotating relative to the rotating angle component 31 and a hinge locking mechanism acting between a locking position and an unlocking position, wherein the rotating angle component 31 and the angle positioning component 32 are respectively connected with two parts needing to be hinged, in the embodiment, the rotating angle component 31 is fixedly connected with a folding arm b2, the angle positioning component 32 is fixedly connected with a main arm b1, so that the folding arm b2 and the main arm b1 can rotate relatively through the connection of the rotating assembly 3, for an aircraft, the most important rotating state is an unfolding state and a folding state, therefore, two groups of clamping parts 311 are arranged on the rotating angle component 31 at intervals in the rotating circumferential direction, one group is an angle position in the folding state, the other group is an angle position in the unfolding state, a positioning part 321 matched with the clamping parts 311 is arranged on the angle positioning component 32, when the rotating angle member 31 and the angle positioning member 32 rotate relatively, the positioning portion 321 is matched with the engaging portion 311 at different angle positions to realize rotating angle positioning;
when the rotating angle piece 31 and the angle positioning piece 32 relatively rotate to the positioning part 321 to be matched with the clamping part 311 in the folded state, the aircraft rotates to the folded state, and when the rotating angle piece 31 and the angle positioning piece 32 relatively rotate to the positioning part 321 to be matched with the clamping part 311 in the unfolded state, the aircraft rotates to the unfolded state;
during the rotation, the hinge locking mechanism is in an unlocking position, so that the rotation angle piece 31 and the angle positioning piece 32 can rotate relatively; and when rotating to target in place, promptly, when location portion 321 and block portion 311 reached the fit state, the operation articulated locking mechanism switch to the locking position, articulated locking mechanism keeps location portion 321 and block portion 311 to be in the fit state and makes unable relative rotation to take place between rotation angle spare 31 and the angle location spare 32 this moment to can make the aircraft keep firm expansion state and the folded state through articulated locking mechanism, ensure the stability of aircraft flight, avoid the fold state of aircraft to take place unexpected switching, improve the reliability.
In this embodiment, the engaging portion 311 is a groove, the positioning portion 321 is a protrusion engaged with the groove, and two sides of the groove along the rotation circumferential direction are inclined slopes, correspondingly, two sides of the protrusion along the rotation circumferential direction are also inclined slopes, or two sides of only one of the groove and the protrusion along the rotation circumferential direction are inclined slopes, and the inclined slopes are used for guiding to improve the smoothness of engagement between the engaging portion 311 and the positioning portion 321, so that during the rotation process, the protruding positioning portion 321 can be smoothly inserted into the groove-shaped engaging portion 311 or withdrawn from the engaging portion 311, the protruding positioning portion 321 and the groove-shaped engaging portion 311 are engaged with each other with high reliability and high precision, thereby ensuring the precision and stability of the aircraft in the folded state and the unfolded state, and the protruding positioning portion 321 and the groove-shaped engaging portion 311 are simple in structure, the processing is convenient, the cost is low, and the realization is easy;
further, in this embodiment, the engaging portion 311 is disposed on the end surface of the angle positioning member 31 near the angle positioning member 32 in the axial direction of rotation, and the positioning portion 321 is correspondingly disposed on the end surface of the angle positioning member 32 near the angle positioning member 31 in the axial direction of rotation, so that the structure is more compact, and the engaging portion 311 and the positioning portion 321 do not occupy the space in the circumferential direction of rotation; when the engaging portion 311 and the positioning portion 321 of this structure are adopted, as long as there is a certain mobility in the rotation axis direction between the rotation angle member 31 and the angle positioning member 32, which may be a gap in the rotation axis direction, or the rotation angle member 31 and the angle positioning member 32 are elastically deformed, the rotation angle member 31 and the angle positioning member 32 can relatively rotate, and when the mobility in the rotation axis direction between the rotation angle member 31 and the angle positioning member 32 is eliminated, the gap in the rotation axis direction between the rotation angle member 31 and the angle positioning member 32 can be eliminated, or the rotation angle member 31 and the angle positioning member 32 are pressed to avoid elastic deformation, the rotation angle member 31 and the angle positioning member 32 can not relatively rotate, so that when the hinge locking mechanism is in the locking position, it can apply an acting force in the rotation axis direction to press the rotation angle member 31 and the angle positioning member 32 together, the function of keeping the positioning part 321 and the clamping part 311 in the matching state can be realized;
specifically, the hinge locking mechanism includes a locking block 33 moving in the direction perpendicular to the rotation axis, the locking block 33 is provided with a driving inclined plane 331 inclined to the rotation axis for pressing the rotation angle member 31 and the angle positioning member 32, when the locking block moves in the direction perpendicular to the rotation axis, the driving inclined plane on the locking block can generate displacement in the rotation axis direction, so that the rotation angle member 31 and the angle positioning member 32 are pressed in the rotation axis direction, and the protruding positioning portion 321 and the groove-shaped engaging portion 311 are more tightly fitted together, at this time, the protruding positioning portion 321 is difficult to withdraw from the groove-shaped engaging portion 311, thereby playing a role of a locking state, so that the aircraft can be locked and maintained in a furled state or an unfolded state, and avoid the accidental displacement in the furled state or unfolded state, when the state of the aircraft needs to be switched, the locking block only needs to be moved reversely.
In this embodiment, the rotating assembly 3 further includes a rotating shaft 34, the inside of the rotating shaft 34 is hollow for routing, that is, the power supply line of the rotor power assembly c is routed from the inside of the rotating shaft 34, the rotating angle component 31 is non-rotatably disposed on the rotating shaft 34, the angle positioning component 32 is rotatably sleeved on the rotating shaft 34, because the rotating angle component 31 is fixed on the folding arm b2, the rotating shaft 34 and the folding arm b2 are non-rotatably fixed and connected, the folding arm b2 is provided with a through hole penetrating up and down, the rotating shaft 34 penetrates into the through hole, a folding arm hinge seat b21 for the rotating shaft 34 to penetrate is disposed on the lower side of the through hole in an attaching manner, so as to improve the structural strength, ensure that the rotating shaft 34 can be stably connected with the folding arm b2, the rotating angle component 31 is disposed on the upper side of the through hole and sleeved on the rotating shaft 34, the lower side of the main, the angle positioning element 32 is fixedly arranged on the lower surface of the through hole of the main arm b1, so that the rotating angle element 31 and the angle positioning element 32 can be attached to each other in the rotating shaft direction, so that the convex positioning part 321 and the concave clamping part 311 can be matched to play a role in positioning the rotating angle, the main arm b1 is of a hollow structure, and a main arm hinge seat b11 for the rotating shaft 34 to penetrate through is arranged in the main arm b1, so that the structural strength of the main arm b1 is improved, and the stability of the rotating connection of the folding arm b2 and the main arm b1 is enhanced;
in order to ensure that the locking block 33 can move stably along the direction vertical to the rotating axial direction, a channel assembly 35 fixed on a main arm hinge seat b11 is arranged in the main arm b1, the path direction of the channel assembly 35 is perpendicular to the axial direction of rotation, specifically, the channel assembly 35 is composed of a pressing seat 351 and a pressing plate 352 sleeved on the rotating shaft 34, the pressing seat 351 and the pressing plate 352 are fixed on the main arm hinge seat b11 through bolts, and the pressing plate 352 is in a structure of being arched in the middle, so that a passage for the movement of the locking block 33 is formed between the pressing seat 351 and the pressing plate 352 in a path direction perpendicular to the rotation axial direction, in this embodiment, the locking block 33 is provided with a through hole, the locking block 33 is also sleeved on the rotating shaft 34, the locking block 33 is located in the channel formed between the pressing seat 351 and the pressing plate 352, the locking block 33 penetrates through the wall surface of the main arm b1, so that the locking block 33 can be conveniently operated to switch between the locking position and the unlocking position;
further, in this embodiment, the locking block 33 is formed by connecting two parts, and both the two parts respectively penetrate through the wall surface of the main arm b1, one end of the locking block 33 penetrating through the main arm b1 is pressed towards the inner side of the main arm b1 to switch from the locking position to the unlocking position, and the other end of the locking block 33 penetrating through the main arm b1 is pressed towards the inner side of the main arm b1 to switch from the unlocking position to the locking position, so that two ends of the locking block 33 can be respectively defined as a locking end and an unlocking end, and the locking end and the unlocking end are in different colors, for example, the unlocking end is green and the locking end is red, which facilitates accurate locking and unlocking operations; in the embodiment, two parallel folding arms b2 are hinged to one main arm b1 at intervals, and the folding arm b2 is hinged to the fuselage to form a parallelogram folding arm structure, the main arm b1 is connected with one folding arm b2 by using the aforementioned rotating component 3 with the hinge locking mechanism, and the main arm b1 is connected with the other folding arm b2 by using a rotating component without the hinge locking mechanism, so that the whole parallelogram folding arm structure can be locked by locking the hinged position of the main arm b1 and one folding arm b2, the stable mechanism state of the folding arm structure is maintained, the occurrence of rotational displacement is avoided, the aircraft is kept in a stable unfolding state and a folding state, and the flying stability of the aircraft is guaranteed;
in this embodiment, the driving inclined plane 331 of the locking block 33 faces upward, the rotating shaft 34 is further sleeved with a pressing block 36 located above the locking block 33, the pressing plate 352 is provided with a through hole through which the pressing block 36 can freely pass along the axial direction of the rotating shaft, the rotating shaft 34 is screwed with a nut 37, the pressing block 36 is locked and abutted on the locking block 33 by the nut 37, in order to ensure that the locking block 33 drives the pressing block 36 smoothly without retardation, a contact position of the pressing block 36 and the locking block 33 is an inclined plane matched with the driving inclined plane 331, when the locking block 33 moves from an unlocking position to a locking position along a direction perpendicular to the axial direction of rotation, the locking block 33 pushes the pressing block 36 to move upward through the driving inclined plane 331, the movement of the locking block 33 along the direction perpendicular to the axial direction of rotation is converted into the movement of the pressing block 36 along the axial direction of rotation through the driving inclined plane 331, so that the pressing block 36 drives the rotating shaft 34, the folding arm b2 is also driven to move upwards to be more close to the main arm b1, the rotating angle piece 31 and the angle positioning piece 32 are pressed together along the rotating axial direction, the convex positioning part 321 is tightly matched with the groove-shaped clamping part 311 and cannot be separated and withdrawn, and therefore the aircraft is locked in an unfolding state or a folding state; when the locking block 33 moves from the locking position to the unlocking position along the direction perpendicular to the rotation axial direction, the additional axial acting force applied to the rotation angle piece 31 and the angle positioning piece 32 is released, the pressure between the rotation angle piece 31 and the angle positioning piece 32 is reduced, the rotation angle piece 31 and the angle positioning piece 32 are reset to a state that the rotation angle piece and the angle positioning piece can rotate relatively, the protruding positioning part 321 can withdraw from the groove-shaped clamping part 311, and therefore the aircraft can be freely switched between a folded state and an unfolded state;
the rotating assembly 3 is further provided with an elastic member 38 with an acting force along the rotating axial direction for pre-pressing the rotating angle member 31 and the angle positioning member 32, in this embodiment, the elastic member 38 is a plurality of spring washers sleeved on the rotating shaft 34, the spring washers are located between the nut 37 and the pressing block 36, the pressing block 36 is freely movable along the rotating shaft 34 in the axial direction, the spring washers elastically press the pressing block 36 on the locking block 33, and simultaneously, the acting force of the spring washers is utilized to elastically press the rotating angle member 31 and the angle positioning member 32 together in the rotating axial direction, so that when the rotating angle member 31 and the angle positioning member 32 rotate relatively, there is an elastically yielding space between the rotating angle member 31 and the angle positioning member 32, and during the rotating process, when the protruding positioning portion 321 is not inserted into the groove-shaped engaging portion 311, the protruding positioning portion 321 abuts against the surface of the rotating angle member 31, that is, the gap between the angle rotating member 31 and the angle positioning member 32 in the axial direction of rotation is increased, and at this time, the elastic member 38 is further compressed to elastically avoid, so that the angle rotating member 31 and the angle positioning member 32 can be ensured to rotate relatively; when the locking block 33 moves from the unlocking position to the locking position along the direction perpendicular to the axial direction of rotation, the locking block 33 pushes the pressing block 36 to move upwards through the driving inclined surface 331 so as to further compress the elastic element 38, and in turn, the elastic element 38 generates larger acting force, so that the rotation angle member 31 and the angle positioning member 32 are pressed together more tightly in the axial direction of rotation, the protruding positioning part 321 is ensured not to withdraw from the groove-shaped clamping part 311, and the stability of the aircraft in the folding state and the unfolding state is ensured.
Example two
As shown in fig. 6, the rotating assembly 3 mainly includes a rotating angle member 31, an angle positioning member 32 rotating relative to the rotating angle member 31, and a hinge locking mechanism acting between a locking position and an unlocking position, the rotating angle member 31 and the angle positioning member 32 are respectively connected to two components to be hinged, in this embodiment, the rotating angle member 31 is fixedly connected to the folding arm b2, and the angle positioning member 32 is fixedly connected to the main arm b1, so that the folding arm b2 and the main arm b1 can rotate relatively by the connection of the rotating assembly 3, two sets of engaging portions 311 are provided on the rotating angle member 31 at intervals in the rotating circumferential direction, one set is an angular position in a folded state, the other set is an angular position in an unfolded state, a positioning portion 321 engaged with the engaging portion 311 is provided on the angle positioning member 32, when the rotating angle member 31 and the angle positioning member 32 rotate relatively, the positioning part 321 is matched with the clamping part 311 at different angle positions to realize the positioning of the rotation angle;
specifically, the section of the rotating angle member 31 in the rotating axial direction is substantially T-shaped, the cap of the T-shaped rotating angle member 31 is inserted into the main arm b1 from a hole formed in the lower portion of the main arm b1, the aperture of the hole is smaller than the cap of the T-shaped rotating angle member 31, the lower portion of the T-shaped rotating angle member 31 is fixedly connected to the folding arm b2, the top surface of the cap of the T-shaped rotating angle member 31 is provided with a groove-shaped engaging portion 311, the main arm b1 is fixedly provided with an angle positioning member 32 opposite to the top surface of the cap of the T-shaped rotating angle member 31, the angle positioning member 32 is provided with a protruding positioning portion 321, the hole of the main arm b1 is provided with an elastic member 38 for elastically pressing the rotating angle member 31 and the angle positioning member 32, the left and right side walls of the main arm b1 are formed with holes and are movably inserted into a locking block 33 having a driving inclined surface 331 inclined in the rotating axial direction, and the driving inclined surface 331 is used, the locking and unlocking are realized by moving the locking block 33 in the left-right direction, and the driving inclined surface 331 is in contact with the cap portion of the T-shaped rotating angle member 31 to drive the rotating angle member 31 to be pressed against the angle positioning member 32, so that the current state of the locking is reliably realized, and the occurrence of displacement is avoided.
EXAMPLE III
As shown in fig. 7, the rotating assembly 3 mainly includes a rotating angle member 31, an angle positioning member 32 rotating relative to the rotating angle member 31, and a hinge locking mechanism acting between a locking position and an unlocking position, the rotating angle member 31 and the angle positioning member 32 are respectively connected to two components to be hinged, two sets of engaging portions 311 are arranged on the rotating angle member 31 at intervals in the rotating circumferential direction, one set is an angular position in a folded state, the other set is an angular position in an unfolded state, a positioning portion 321 cooperating with the engaging portions 311 is arranged on the angle positioning member 32, and when the rotating angle member 31 and the angle positioning member 32 rotate relatively, the positioning portion 321 cooperates with the engaging portions 311 at different angular positions to realize rotating angle positioning;
in this embodiment, the engaging portion 311 is disposed on the circumferential periphery of the rotation angle member 31, the engaging portion 311 is specifically a groove on the circumferential periphery of the rotation angle member 31, the positioning portion 321 is an elastic protruding plate engaged with the groove-shaped engaging portion 311, the hinge locking mechanism is a locking pin moving upward perpendicular to the rotation axis, the locking pin moves to abut against the elastic protruding plate-shaped positioning portion 321, so that the positioning portion 321 of the elastic protruding plate is tightly engaged with the groove-shaped engaging portion 311, and the elastic protruding plate is abutted by the locking pin and cannot be elastically retracted, thereby effectively locking the current state, avoiding displacement and avoiding change of the rotation angle state.
The above is only a preferred embodiment of the present invention, and it should be noted that the above preferred embodiment should not be considered as limiting the present invention, and the protection scope of the present invention should be subject to the scope defined by the claims. It will be apparent to those skilled in the art that various modifications and enhancements can be made without departing from the spirit and scope of the invention, and such modifications and enhancements are intended to be within the scope of the invention.
Claims (10)
1. The utility model provides a rotating assembly, its characterized in that, includes rotation angle spare (31), for rotation angle spare (31) pivoted angle location spare (32) and the articulated locking mechanism of action between locking position and unblock position, rotation angle spare (31) are gone up and are rotated the interval in the week and be provided with at least one block portion (311), angle location spare (32) on be provided with block portion (311) complex location portion (321), articulated locking mechanism keep location portion (321) and block portion (311) to be in the fit state when being in the locking position.
2. The rotating assembly according to claim 1, wherein the engaging portion (311) is a groove, and the positioning portion (321) is a protrusion engaged with the groove.
3. The rotating assembly according to claim 1, wherein the engaging portion (311) is disposed on an end surface of the rotating angle member (31) close to the angle positioning member (32) in the rotating axial direction, and the positioning portion (321) is correspondingly disposed on an end surface of the angle positioning member (32) close to the rotating angle member (31) in the rotating axial direction.
4. The rotating assembly according to claim 3, wherein the hinge locking mechanism applies a force in the axial direction of rotation when in the locking position to press the rotating angle member (31) against the angle positioning member (32) to maintain the positioning portion (321) and the engaging portion (311) in the engaged state.
5. Rotating assembly according to claim 3, wherein the hinge locking mechanism comprises a locking block (33) movable in a direction perpendicular to the axis of rotation, the locking block (33) being provided with a driving ramp (331) inclined in the axial direction of rotation for pressing the angle of rotation member (31) against the angle positioning member (32).
6. The rotating assembly according to claim 5, wherein the hinge locking mechanism further comprises a channel assembly (35) having a path direction perpendicular to the rotating axial direction, and the locking block (33) slides along the channel assembly (35) to switch between the locking position and the unlocking position for pressing the rotating angle member (31) and the angle positioning member (32) in the rotating axial direction.
7. The rotating assembly according to claim 5, further comprising a rotating shaft (34), wherein one of the rotating angle member (31) and the angle positioning member (32) is non-rotatably disposed on the rotating shaft (34), and the other one is rotatably disposed on the rotating shaft (34).
8. Rotating assembly according to claim 7, further comprising a resilient member (38) acting in the axial direction of rotation for pre-stressing the rotating angle member (31) and the angle positioning member (32).
9. The rotating assembly according to claim 8, further comprising a nut (37), wherein the rotating angle member (31), the angle positioning member (32), the locking block (33), the elastic member (38) and the nut (37) are sequentially sleeved on the rotating shaft (34), one end of the elastic member (38) abuts against the nut (37), and the other end of the elastic member exerts an axial force on the locking block (33).
10. An aircraft, characterized in that a rotary folding structure is formed by a rotary assembly according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020787332.XU CN212448036U (en) | 2020-05-13 | 2020-05-13 | Rotating assembly and aircraft adopting same |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111422345A (en) * | 2020-05-13 | 2020-07-17 | 成都纵横大鹏无人机科技有限公司 | Rotating assembly |
| CN113581477A (en) * | 2021-06-29 | 2021-11-02 | 成都纵横大鹏无人机科技有限公司 | Functional module mounting structure and aircraft adopting same |
| CN114347738A (en) * | 2022-01-12 | 2022-04-15 | 广东汇天航空航天科技有限公司 | Arm mechanism and flight device |
| CN113581477B (en) * | 2021-06-29 | 2024-04-26 | 成都纵横大鹏无人机科技有限公司 | Function module mounting structure and adopt its aircraft |
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2020
- 2020-05-13 CN CN202020787332.XU patent/CN212448036U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111422345A (en) * | 2020-05-13 | 2020-07-17 | 成都纵横大鹏无人机科技有限公司 | Rotating assembly |
| CN113581477A (en) * | 2021-06-29 | 2021-11-02 | 成都纵横大鹏无人机科技有限公司 | Functional module mounting structure and aircraft adopting same |
| CN113581477B (en) * | 2021-06-29 | 2024-04-26 | 成都纵横大鹏无人机科技有限公司 | Function module mounting structure and adopt its aircraft |
| CN114347738A (en) * | 2022-01-12 | 2022-04-15 | 广东汇天航空航天科技有限公司 | Arm mechanism and flight device |
| CN114347738B (en) * | 2022-01-12 | 2023-06-02 | 广东汇天航空航天科技有限公司 | Arm mechanism and flight device |
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