CN216887201U - Propeller quick assembly disassembly structure and aircraft that is equipped with this structure - Google Patents
Propeller quick assembly disassembly structure and aircraft that is equipped with this structure Download PDFInfo
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- CN216887201U CN216887201U CN202122254501.0U CN202122254501U CN216887201U CN 216887201 U CN216887201 U CN 216887201U CN 202122254501 U CN202122254501 U CN 202122254501U CN 216887201 U CN216887201 U CN 216887201U
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Abstract
The utility model discloses a propeller quick disassembly and assembly structure and an aircraft with the same, and is characterized in that: the locking fuse is provided with a first boss, the button is provided with a first groove, and the first boss is matched with the first groove; go up the inclined plane and match with the upper portion fitting surface of screw propeller blade, the upper portion fitting surface that the upper slope can compress tightly the paddle and correspond at paddle dismouting in-process, the lower inclined plane matches with the lower part fitting surface of screw propeller blade, the decline inclined plane of button is packed into and is popped out the in-process at the paddle, can realize through paddle up-and-down motion that the button carries out the function that links according to the lower part fitting surface, the propeller hub is rectangular shape, the button makes the button compress tightly paddle hub both ends through corresponding complex upper portion inclined plane or lower part inclined plane when the paddle pushes down the laminating to the base. The propeller quick dismounting structure and the aircraft with the propeller quick dismounting structure are simple in dismounting operation, high in safety and safety degree, capable of reducing abrasion, saving cost and prolonging service life of products.
Description
Technical Field
The utility model relates to the technical field of aircraft propeller dismounting, in particular to a propeller quick dismounting structure and an aircraft with the same.
Background
The propeller is a device which rotates in the air or water by means of blades and converts the rotating power of an engine into propulsive force, two or more blades are connected with a hub, the backward surface of each blade is a propeller with a spiral surface or a similar spiral surface, the propeller is an important structure of aircrafts such as helicopters, generally, the propeller has advancing speed besides rotation, and the propeller is particularly important in the aircrafts such as helicopters. Existing propellers typically have one or more of the following characteristics during use. The blade root is mostly in a circular outer contour, so that the blade root is suitable for small-size blades, and if the blade root is used for large-size blades, a lot of unnecessary structural weight needs to be added; the transition modeling design between the blade root and the quick-release structure is not beneficial to the local stress of the blade root and cannot be used for large blades; for the propeller made of plastic, the structure of the propeller hub is too complex, the degree of responsibility of the mold structure and the production and maintenance cost of the mold are increased for a plastic injection mold, and the service life of the mold is greatly reduced; the quick-release contact surface is easy to wear; the requirement on the accuracy of machining errors is high, gaps are easily generated on the contact surface of the quick-release structure, the gaps can cause collision and abrasion, and the gaps can also generate vibration, so that the safety and the service life of a motor, even an aircraft or a related carrier structure are influenced; the quick-dismantling structure of the propeller is provided with the spring, the strength of the spring causes the contradiction between the firmness degree of the structure and the strength of the labor spent in the installation process, the operation in the quick-dismantling process is not convenient enough, and the time is not really saved; the quick-release structure is easy to damage due to misoperation by most inexperienced users; the concentric positioning of the propeller and the rotating shaft is not accurate enough, and the dynamic balance stability of the propeller during operation is influenced; the propeller is not parallel to the mounting plane, and the contact area is too small, so that aerodynamic balance of the propeller during running is influenced; the propeller needs to operate under a complex working condition with large vibration, and most of the prior art schemes lack a safety design to ensure that the quick-release structure cannot be accidentally loosened during vibration; in this intelligent era, the prior art solutions all stay at the level of solving the problems with the original mechanical structure, and do not fully utilize the new intelligent characteristics to comprehensively improve the safety of the quick-release structure.
Disclosure of Invention
The utility model aims to: overcome the not enough of prior art existence, solve the problem that exists among the prior art, provide a screw quick assembly disassembly structure and be equipped with the aircraft of this structure, it has solved one or more problems that exist among the prior art, has reached better effect.
The technical scheme of the utility model is as follows:
the utility model provides a screw quick assembly disassembly structure which characterized in that: it comprises a locking safety, a button and a base, wherein the base can be arranged on a motor front cover or integrated on the motor front cover of a propeller,
the locking fuse is provided with a first boss, the button is provided with a first groove, and the first boss is matched with the first groove;
one side of the button is provided with an upper inclined plane and a lower inclined plane, the upper inclined plane is matched with the upper matching surface of the propeller blade, the upper inclined plane can compress the upper matching surface corresponding to the blade in the blade dismounting process, the lower inclined plane is matched with the lower matching surface of the propeller blade, the lower inclined plane of the button can realize the function of linkage of the button according to the lower matching surface through the up-and-down motion of the blade in the blade mounting and ejecting process,
the propeller hub is in a long strip shape, and the button presses two ends of the propeller hub tightly through the corresponding matched inclined planes when the propeller blade is pressed down and attached to the base;
the base both sides are provided with first pivot hole, and the button setting is provided with the second pivot hole that corresponds with first pivot hole in the both sides of base on the button, and first pivot hole and second pivot hole can be passed in the pivot, and the button is spacing in the base both sides and can be in the set angle free rotation through the pivot.
As a further improvement of the scheme, the position of the upper inclined plane close to the center and the position far away from the center are high; the lower inclined plane and the lower matching surface of the propeller blade are low at the position close to the center and high at the position far away from the center.
As the further improvement of this scheme, the upper portion fitting surface and the button cooperation of paddle compress tightly to reserve corresponding opening and give the button and pass through, there is the circular port in the middle part to be used for fixing and can make the locking insurance rotate at the cooperation position, and paddle middle part platform has set up 4 spherical recess for realize the location of locking and two kinds of positions of unblanking with the spherical protrusion of locking insurance bottom.
As the further improvement of the scheme, one part of the locking safety is inserted into the middle hole in the middle of the paddle, the locking safety and the paddle cannot be easily separated in an assembly state, and in the process that the paddle and the locking safety assembly are pressed into the base, the middle hole in the inner part of the rod body extending out of the lower part of the locking safety and the cylindrical boss in the middle of the base are in positioning fit, so that the paddle assembly and the motor base assembly are concentrically centered.
As a further improvement of the scheme, the two sides of the base are provided with upward limiting bosses, the middle part of the paddle is provided with downward limiting grooves, and the limiting bosses are matched with the limiting grooves in the middle part of the paddle.
As a further improvement of the scheme, the limiting boss is a long circular boss, and the limiting groove is a long circular hole groove.
As a further improvement of the scheme, a second boss is arranged at a position, close to the center, of the locking fuse, a second groove matched with the second boss is formed in the paddle, and the second boss can be matched and locked with the second groove.
As a further improvement of the scheme, the center of the base is provided with a central circular boss, and the lower part of the locking fuse is provided with a rod body middle hole matched with the central circular boss.
As a further improvement of the scheme, the bottom plane of the hub of the blade and the upper surface mounting plane of the base are contacted with the positioning device.
As a further improvement of the scheme, the base is provided with a center hole facing downwards, the groove is matched with the motor shaft in a positioning mode, and the base is fixed with the motor through screws.
The utility model provides an aircraft that is equipped with aforementioned screw quick assembly disassembly structure which characterized in that: the propeller comprises a propeller, a motor and a propeller quick-dismounting structure, wherein the propeller comprises blades and a propeller hub, the propeller hub is in a strip shape, and the length direction of the propeller hub is consistent with the central line direction of the blades of the propeller;
the propeller quick assembly disassembly structure comprises a locking safety device, a button and a base, wherein the base can be arranged on a motor front cover or integrated on the motor front cover of the propeller,
the propeller blade is provided with an upper matching surface and a lower matching surface close to the propeller seat, the upper matching surface is matched with the upper inclined surface of the button, the lower matching surface is matched with the lower inclined surface of the button,
the locking device comprises a base, a locking safety piece, a locking groove, a first rotating shaft hole, a second boss and a second boss, wherein the base is provided with the first rotating shaft hole and the limiting boss, the middle part of the paddle is provided with the limiting groove facing downwards, the limiting boss is matched with the limiting groove in the middle part of the paddle, the button is arranged on two sides of the base, the button is provided with the second rotating shaft hole corresponding to the first rotating shaft hole, the rotating shaft can penetrate through the first rotating shaft hole and the second rotating shaft hole, the button is limited on two sides of the base through the rotating shaft and can freely rotate within a set angle, the locking safety piece is provided with the second boss close to the central position, the paddle is provided with the second groove matched with the second boss, and the second boss can be matched and locked with the second groove; the center of the base is provided with a central circular boss, and the lower part of the locking fuse is provided with a rod body middle hole matched with the central circular boss.
The utility model has the advantages that:
the propeller quick dismounting structure and the aircraft with the propeller quick dismounting structure are simple in dismounting operation, high in safety and safety degree, capable of reducing abrasion, saving cost and prolonging service life of products.
Drawings
The utility model is further described with reference to the following figures and examples:
FIG. 1 is a schematic illustration of a prior art propeller blade and hub installation.
FIG. 2 is a schematic view of the mounting of the propeller blades and hub of an aircraft having a propeller quick disconnect structure according to the present invention.
Fig. 3 is a schematic view of the propeller quick-release structure of the present invention.
Fig. 4 is a schematic cross-sectional view of the propeller quick-release structure of the present invention.
FIG. 5 is an exploded pictorial illustration of a propeller blade installation for an aircraft having a propeller quick disconnect structure in accordance with the present invention.
Fig. 6 is an enlarged view of a portion of fig. 5.
FIG. 7 is a schematic view of the mounting and locking condition of the propeller blades of the aircraft with the propeller quick release structure of the present invention.
FIG. 8 is a schematic view of the rotor blades of the aircraft with the rotor quick release structure of the present invention in an unlocked state.
FIG. 9 is a schematic view of the state of the push button pressed by the propeller blade of the aircraft with the propeller quick-release structure according to the present invention.
Fig. 10 is an enlarged view of a portion of fig. 9.
Fig. 11 is a schematic view of the complete disassembly state of the propeller blades of the aircraft provided with the propeller quick-disassembly structure.
Wherein: 1. the locking safety 101, the first boss 102, the second boss 2, the blade 201, the first groove 202, the upper mating surface 203, the lower mating surface 204, the limiting groove 3, the button 301, the upper inclined surface 302, the lower inclined surface 4, the base 401, the rotation center 402, the limiting boss 5, the rotating shaft 6 and the hub.
Detailed Description
The technical solution of the present invention will be described in detail below with reference to the accompanying drawings and preferred embodiments.
As shown in fig. 1-11, the present invention discloses a propeller quick dismounting structure, which comprises a locking fuse 1, a button 3, and a base 4, wherein the base 4 can be installed on a motor front cover or integrated on the motor front cover of the propeller, the locking fuse 1 is provided with a first boss 101, the button 3 is provided with a first groove 201, and the first boss 101 is matched with the first groove 201; an upper inclined plane 301 and a lower inclined plane 302 are arranged on one side of the button 3, the upper inclined plane 301 is matched with an upper matching surface 202 of the propeller blade 2, the upper inclined plane 301 can press the upper matching surface 202 corresponding to the blade 2 in the process of assembling and disassembling the blade 2, the lower inclined plane 302 is matched with a lower matching surface 203 of the propeller blade 2, the lower inclined plane 302 of the button 3 can realize the linkage function of the button 3 according to the lower matching surface 203 through the up-and-down movement of the blade 2 in the process of loading and ejecting the blade 2, the hub 6 is in a long strip shape, and the button 3 can press two ends of the hub 6 of the blade 2 through the upper inclined plane and the lower inclined plane which are correspondingly matched when the blade 2 is pressed and attached to the base 4; base 4 both sides are provided with 5 holes in first pivot and spacing boss 402, button 3 sets up the both sides at base 4, be provided with 5 holes in the second pivot that correspond with 5 holes in first pivot on the button 3, 5 holes in first pivot 5 holes and the 5 holes in second pivot can be passed to pivot 5, button 3 is spacing in base 4 both sides and can be in the set angle free rotation through pivot 5, so 2 or take out paddle 2 are impressed or paddle 2 is taken out, need not go to rotate button 3 with the hand, because button 3 can realize the linkage and press the direction rotation of corresponding needs according to the operation about lower part fitting surface 203 and paddle 2, the complexity of simplified operation. The contact sliding between the rotating process of the button 3 and the inclined surface of the paddle 2 is not strongly frictional, and the relative sliding between the contact surfaces is reduced as much as possible, so that the abrasion between the contact surfaces is reduced. Through button 3 upper and lower inclined plane 302 and paddle 2 fitting surface (inclined plane) of well-designed, can realize that paddle 2 packs into and does not need direct touching or operating button 3 of in-process of taking out, because inclined plane cooperation between them adds button 3 rotational degree of freedom, when paddle 2 reciprocated, button 3 can follow the rotation in step, the operation complexity that has significantly reduced. Pressing the paddle 2 to the end will naturally bring the button 3 to the pressing position by the lower inclined plane 302 so that the upper inclined plane 301 presses the paddle 2, and then the locking safety 1 is turned to the locking position, and the paddle 2 is quickly assembled.
As a further improvement of the scheme, the position of the upper inclined plane 301 close to the center and the position far away from the center are high, and the upper matching surface 202 of the propeller blade 2 is lower; the lower inclined surface 302 and the lower engagement surface 203 of the propeller blade 2 are located low near the center and high far from the center. The locking insurance 1 forms a complete and mutually balanced force transmission path with the buttons 3 on the two sides and the inclined plane on the upper part of the blade 2 after being locked, once the blade 2 generates two lateral middle bending moments after rotating, the two buttons 3 on the two sides can be extruded to rotate towards the middle through the inclined plane, and then the two ends of the locking insurance 1 are all propped against, so that the whole structure per se forms a self-locking mode under the working state, and is more fastened than an assembled quick-release structure which is not in the working rotating state, the middle locking insurance 1 is more difficult to accidentally loosen due to vibration factors, and the larger the pulling force of the blade 2 is, the larger the clamping force on the locking insurance 1 is, and the more firm the locking is, and the more the loosening is avoided due to vibration.
As the further improvement of this scheme, the upper portion fitting surface 202 of paddle 2 compresses tightly with the cooperation of button 3 to reserve corresponding opening and pass through for button 3, there is the circular port in the middle part of button 3 to be used for fixing and can make locking insurance 1 rotate at the cooperation position, paddle 2 middle part platform has set up 4 spherical recess, be used for realizing the location of locking and two kinds of positions of unblanking with the spherical arch of locking insurance 1 bottom, made things convenient for the operation of locking and unblock.
As a further improvement of the scheme, a part of the locking safety 1 is inserted into a middle hole in the middle of the paddle 2, the locking safety 1 and the paddle 2 are in an assembly state and cannot be easily separated, and in the process that the paddle 2 and the locking safety 1 are pressed into the base 4, the middle hole in the rod body extending out of the lower portion of the locking safety 1 is in positioning fit with a cylindrical boss in the middle of the base 4, so that the paddle 2 assembly and the motor-base 4 assembly are concentrically centered.
As a further improvement of the scheme, the two sides of the base 4 are provided with upward limiting bosses 402, the middle part of the paddle 2 is provided with downward limiting grooves 204, the limiting bosses 402 are matched with the limiting grooves 204 in the middle part of the paddle 2 to position the paddle 2, and the limiting bosses 402 are matched with the limiting grooves 204 to transmit torque required by the paddle 2.
As a further improvement of the scheme, the limiting boss 402 is a long circular boss, and the limiting groove 204 is a long circular hole groove. The oblong groove on the lower surface of the hub 6 of the blade 2 is matched with the oblong boss on the corresponding position of the base 4 for circumferential positioning, and simultaneously, the matching can also effectively transfer the torque load between the blade 2 and the base 4. Allowing the torque load and the later mentioned tensile load to be separated. Because the long circular groove and the boss are far away from the rotation center 401, the stress level of the matching structure when bearing torque can be greatly improved, the reliability of the structure is enhanced, and the service life is prolonged.
As a further improvement of the scheme, a second boss 102 is arranged at a position, close to the center, of the locking fuse 1, a second groove matched with the second boss 102 is arranged on the blade 2, and the second boss 102 can be matched and locked with the second groove. The second groove can be an oblong groove, the second boss 102 can be an oblong boss, the oblong groove in the lower surface of the hub 6 of the blade 2 is matched with the oblong boss in the corresponding position of the base 4 for circumferential positioning, and meanwhile, the matching can also effectively transfer torque load between the blade 2 and the base 4. Allowing the torque load and the later mentioned tensile load to be separated. Because the long circular groove and the boss are far away from the rotation center 401, the stress level of the matching structure when bearing torque can be greatly improved, the reliability of the structure is enhanced, and the service life is prolonged.
As a further improvement of the scheme, the center of the base 4 is provided with a central circular boss, and the lower part of the locking fuse 1 is provided with a rod body middle hole matched with the central circular boss. The central hole of the lower rod body of the locking insurance 1 and the central circular boss on the base 4 are concentrically centered and positioned, so that the problem of dynamic balance caused by inaccurate positioning of the paddle 2 is reduced as much as possible.
As a further improvement of this solution, the bottom plane of the hub 6 of the blade 2 and the upper surface mounting plane of the base 4 contact the positioning means. The plane contact positioning device can ensure that the paddle 2 is installed at a correct position, the paddle 2 is tightly matched with the top plane of the motor, and the problem of unbalanced air force is reduced as much as possible.
The contact sliding between the rotating process of the button 3 and the inclined surface of the paddle 2 is not strongly frictional, and the relative sliding between the contact surfaces is reduced as much as possible, so that the abrasion between the contact surfaces is reduced. Through button 3 inclined plane 302 and paddle 2 inclined plane about meticulously designed, can realize that paddle 2 packs into and does not need direct touching or operating button 3 with the in-process of taking out, because inclined plane cooperation between them adds button 3 rotational degree of freedom, and when paddle 2 reciprocated, button 3 can follow the rotation in step, the operation complexity that has significantly reduced. Pressing the paddle 2 to the end will naturally bring the button 3 to the pressing position by the lower inclined plane 302 so that the upper inclined plane 301 presses the paddle 2, and then the locking safety 1 is turned to the locking position, and the paddle 2 is quickly assembled.
As a further improvement of the scheme, the base 4 is provided with a center hole facing downwards, the groove is matched with the motor shaft in a positioning mode, and the base 4 is fixed with the motor through screws. The base 4 is centrally positioned with the motor shaft through a center hole of the downward surface and then tightened by a fastening screw. Furthermore, the quick-release structure of the base 4 can be directly integrated on the front end cover of the motor, so that the center positioning and the screw fastening are omitted, and the whole structure can save part of weight and processing cost.
An aircraft provided with the propeller quick-dismounting structure comprises a propeller, a motor and the propeller quick-dismounting structure, wherein the propeller comprises blades 2 and a propeller hub 6, the propeller hub 6 is long in strip shape, and the length direction of the propeller hub is consistent with the direction of the central line of the propeller blades 2; the propeller quick disassembly and assembly structure comprises a locking protector 1, a button 3 and a base 4, wherein the base 4 can be arranged on a motor front cover or integrated on the motor front cover of a propeller, an upper matching surface 202 and a lower matching surface 203 are arranged on a propeller blade 2 close to a propeller seat, the upper matching surface 202 is matched with an upper inclined surface 301 of the button 3, the lower matching surface 203 is matched with a lower inclined surface 302 of the button 3, a first rotating shaft 5 hole and a limiting boss 402 are arranged on two sides of the base 4, a downward limiting groove 204 is arranged in the middle of the blade 2, the limiting boss 402 is matched with the limiting groove 204 in the middle of the blade 2, the button 3 is arranged on two sides of the base 4, a second rotating shaft 5 hole corresponding to the first rotating shaft 5 hole is arranged on the button 3, the rotating shaft 5 can penetrate through the first rotating shaft 5 hole and the second rotating shaft 5 hole, the button 3 is limited on two sides of the base 4 through the rotating shaft 5 and can freely rotate within a set angle, a second boss 102 is arranged at a position, close to the center, of the locking fuse 1, a second groove matched with the second boss 102 is formed in the blade 2, and the second boss 102 can be matched and locked with the second groove; the center of the base 4 is provided with a central circular boss, and the lower part of the locking fuse 1 is provided with a rod body middle hole matched with the central circular boss. The propeller root hub 6 of the propeller with the quick-release structure in the prior art is in a circular outline, if the size is to be enlarged, the scheme is required to be carried out according to the circular diameter, and unnecessary structural volume and weight are required to be increased. The stress level of the root of the blade 2 is determined by the transition position of the hub 6 and the root of the blade 2, the structural quality of the hub 6 is small enough as far as possible in the transition region of the blade 2 at the same interval, the middle part of the prior art scheme is the circular hub 6, and if the transition region is expanded towards the two ends of the blade 2, the circular diameter of the hub 6 can be increased, and the stress level of the root transition region of the blade 2 can be improved by moving the transition region towards the two sides only by lengthening the elongated hub 6. The design of the long-strip-shaped propeller hub 6 is adopted, and the two buttons 3 which can rotate in a certain range enable the buttons 3 to tightly press two ends of the propeller hub 6 of the propeller blade 2 through the corresponding matched inclined planes when the propeller blade 2 is pressed and attached to the base 4.
As shown in fig. 6-9, which are schematic diagrams of the mounting and locking states of the propeller blades 2 of the aircraft with the propeller quick-dismounting structure, and are working states after the propeller clamps are mounted and locked, as shown in fig. 7-8, the locking insurance 1 is rotated by hand for 90 degrees around the central shaft, so that insurance locking can be released, the insurance locking and rotating press block matching groove is used for being conveniently clamped to the locking position during manual operation, and the first groove 201 and the first bulge have certain interference fit so as to prevent the whole blade 2 assembly from being loosened due to vibration during working operation; pressing one side of the top of the button 3 close to the center, rotating and tilting the button 3 around the steel shaft, and enabling the blade 2 to be jacked upwards by the button 3 and the lower matching surface 203 of the blade 2. As shown in fig. 8, the hand grasps the main body of the blade 2 and moves upward to be completely separated from the base 4, and the blade 2 completes the detaching action. The locking insurance 1 rotates to the locking position and can lock the buttons 3 on two sides so that the buttons 3 on two sides are in rigid contact back to back and transfer force, the locking insurance 1 can ensure that the two ends of the insurance can press the upper surfaces of the buttons 3 on two sides forcibly through the optimized design of dimensional tolerance after the insurance is locked in place, and then the buttons 3 can completely press the upper inclined surfaces on two sides of the paddle 2.
The whole quick-release structure has triple insurance, and the first and second insurance are the bulges at both ends of the locking insurance 1 and the spherical bulges at the lower surface, which are respectively matched and locked with the groove at the head of the button 3 and the spherical groove at the upper surface of the middle part of the paddle 2. The third failsafe is the effect of self-locking of the entire blade 2 under the action of aerodynamic forces in the operating state described above. Thus, the triple safety guarantees that the quick release structure cannot be loosened due to vibration in the working state.
The contact sliding between the rotating process of the button 3 and the inclined surface of the paddle 2 is not strongly frictional, and the relative sliding between the contact surfaces is reduced as much as possible, so that the abrasion between the contact surfaces is reduced. Through button 3 inclined plane 302 and paddle 2 inclined plane about meticulously designed, can realize that paddle 2 packs into and does not need direct touching or operating button 3 with the in-process of taking out, because inclined plane cooperation between them adds button 3 rotational degree of freedom, and when paddle 2 reciprocated, button 3 can follow the rotation in step, the operation complexity that has significantly reduced. Pressing the paddle 2 to the end, the button 3 naturally presses the paddle 2 through the lower inclined plane 302 to the pressing position so that the upper inclined plane 301 presses the paddle 2, and then the locking safety 1 is rotated to the locking position, so that the paddle 2 is quickly assembled.
The locking insurance 1 forms a complete and mutually balanced force transmission path with the buttons 3 on the two sides and the inclined plane on the upper part of the blade 2 after being locked, once the blade 2 generates two lateral middle bending moments after rotating, the two buttons 3 on the two sides can be extruded to rotate towards the middle through the inclined plane, and then the two ends of the locking insurance 1 are all propped against, so that the whole structure per se forms a self-locking mode under the working state, and is more fastened than an assembled quick-release structure which is not in the working rotating state, the middle locking insurance 1 is more difficult to accidentally loosen due to vibration factors, and the larger the pulling force of the blade 2 is, the larger the clamping force on the locking insurance 1 is, and the more firm the locking is, and the more the loosening is avoided due to vibration.
The space between the position of the propeller blade 2 and the propeller quick assembly disassembly structure for transmitting the pulling force and the rotating center 401 of the propeller blade 2 can be farther than the prior art, and the contact area can be larger. Further away means that the problem of stress concentration at the root of the blade 2 in prior art solutions is minimized with respect to the forces at the root of the blade 2. The aerodynamic forces generated by the same outer section of the blade 2 are the same, as compared to the lever principle, since the button 3, which is located farther from the center, can be arranged to press against the inclined plane of the blade 2, the longer the lever distance, the smaller the force required to overcome the same bending moment relative to the center. This is the most significant improvement over prior art solutions.
While the utility model has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the spirit and scope of the utility model. The present invention is not intended to be limited to the specific embodiments disclosed herein, but other embodiments falling within the scope of the appended claims are intended to be within the scope of the present invention. The utility model has various embodiments, and all technical solutions formed by adopting equivalent transformation or equivalent transformation are within the protection scope of the utility model.
Claims (10)
1. The utility model provides a screw quick assembly disassembly structure which characterized in that: it comprises a locking safety, a blade, a propeller hub, a button and a base, wherein the base can be arranged on a motor front cover or integrated on the motor front cover of the propeller,
the locking fuse is provided with a first boss, the button is provided with a first groove, and the first boss is matched with the first groove;
one side of the button is provided with an upper inclined plane and a lower inclined plane, the upper inclined plane is matched with the upper matching surface of the propeller blade, the upper inclined plane can compress the upper matching surface corresponding to the blade in the blade dismounting process, the lower inclined plane is matched with the lower matching surface of the propeller blade, the lower inclined plane of the button can realize the function of linkage of the button according to the lower matching surface through the up-and-down motion of the blade in the blade mounting and ejecting process,
the propeller hub is in a long strip shape, and the button presses two ends of the propeller hub through the upper inclined surface or the lower inclined surface which is correspondingly matched when the propeller blade is pressed down and attached to the base;
the base both sides are provided with first pivot hole, and the button setting is provided with the second pivot hole that corresponds with first pivot hole in the both sides of base on the button, and first pivot hole and second pivot hole can be passed in the pivot, and the button is spacing in the base both sides and can be in the set angle free rotation through the pivot.
2. The propeller quick detach structure of claim 1, wherein: the upper inclined plane and the upper matching surface of the propeller blade are low at the position close to the center and high at the position far away from the center; the lower inclined plane and the lower matching surface of the propeller blade are low at the position close to the center and high at the position far away from the center.
3. The propeller quick detach structure of claim 1, wherein: the upper portion fitting surface and the button cooperation of paddle compress tightly to reserve corresponding opening and let the button pass through, there is the circular port in the paddle middle part to be used for fixing and can make the locking insurance rotate at the cooperation position, paddle middle part platform sets up four spherical recess, is used for realizing the location of locking and two kinds of positions of unblanking with the spherical protrusion of locking insurance bottom.
4. The propeller quick detach structure of claim 1, wherein: the locking insurance part inserts the mesopore in paddle middle part, and the locking insurance can not be separated easily with the paddle in the assembled state, and in the paddle and the locking insurance assembly process of impressing on the base, the lower part of locking insurance stretches out the inside mesopore of the body of rod can carry out positioning fit with the cylindrical boss in base middle part, ensures that paddle assembly and motor base assembly are concentric centering.
5. The propeller quick detach structure of claim 1, wherein: the base both sides set up spacing boss up, and the paddle middle part sets up spacing recess down, spacing boss and the cooperation of the spacing recess at paddle middle part.
6. The propeller quick detach structure of claim 5, wherein: the limiting boss is an oblong boss, and the limiting groove is an oblong hole groove.
7. The propeller quick detach structure of claim 1, wherein: the locking insurance is close to central point and puts and set up the second boss, the paddle be provided with the second recess that the second boss matches, the second boss can coordinate the locking with the second recess.
8. The propeller quick detach structure of claim 1, wherein: the center of the base is provided with a central circular boss, and the lower part of the locking fuse is provided with a rod body middle hole matched with the central circular boss.
9. The propeller quick detach structure of claim 1, wherein: a plane contact positioning device is arranged on the bottom plane of the hub of the blade and the upper surface of the base; the base is provided with a center hole facing downwards, the groove is matched with the motor shaft in a positioning mode, and the base is fixed with the motor through screws.
10. An aircraft provided with a propeller quick release structure according to any one of claims 1 to 9, characterized in that: the propeller comprises a propeller, a motor and a propeller quick-dismounting structure, wherein the propeller comprises blades and a propeller hub, the propeller hub is in a strip shape, and the length direction of the propeller hub is consistent with the central line direction of the blades of the propeller;
the propeller quick disassembly and assembly structure comprises a locking safety, a button and a base, wherein the base can be arranged on a motor front cover or integrated on the motor front cover of the propeller,
the propeller blade is provided with an upper matching surface and a lower matching surface close to the propeller seat, the upper matching surface is matched with the upper inclined surface of the button, the lower matching surface is matched with the lower inclined surface of the button,
the locking device comprises a base, a locking safety piece, a locking groove, a first rotating shaft hole, a second boss and a second boss, wherein the base is provided with the first rotating shaft hole and the limiting boss, the middle part of the paddle is provided with the limiting groove facing downwards, the limiting boss is matched with the limiting groove in the middle part of the paddle, the button is arranged on two sides of the base, the button is provided with the second rotating shaft hole corresponding to the first rotating shaft hole, the rotating shaft can penetrate through the first rotating shaft hole and the second rotating shaft hole, the button is limited on two sides of the base through the rotating shaft and can freely rotate within a set angle, the locking safety piece is provided with the second boss close to the central position, the paddle is provided with the second groove matched with the second boss, and the second boss can be matched and locked with the second groove; the center of the base is provided with a central circular boss, and the lower part of the locking fuse is provided with a rod body middle hole matched with the central circular boss.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122254501.0U CN216887201U (en) | 2021-09-17 | 2021-09-17 | Propeller quick assembly disassembly structure and aircraft that is equipped with this structure |
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| CN202122254501.0U CN216887201U (en) | 2021-09-17 | 2021-09-17 | Propeller quick assembly disassembly structure and aircraft that is equipped with this structure |
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| CN216887201U true CN216887201U (en) | 2022-07-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815842A (en) * | 2021-09-17 | 2021-12-21 | 南昌三瑞智能科技有限公司 | Propeller quick assembly disassembly structure and aircraft that is equipped with this structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815842A (en) * | 2021-09-17 | 2021-12-21 | 南昌三瑞智能科技有限公司 | Propeller quick assembly disassembly structure and aircraft that is equipped with this structure |
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Address after: Manufacturing Center, Building D, No. 888, Tianxiang North Avenue, Nanchang High-tech Industrial Development Zone, Nanchang City, Jiangxi Province 330000 Patentee after: Nanchang Sanrui Intelligent Technology Co.,Ltd. Address before: 330000 Room 101, 33, Nanchang Jiahai Industrial Park, 2799 Tianxiang Avenue, Nanchang hi tech Industrial Development Zone, Nanchang City, Jiangxi Province Patentee before: Nanchang SanRui Intelligent Technology Co.,Ltd. |
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