WO2016066009A1 - 旋翼飞行器及电机散热结构、机臂与机身的连接结构和脚架拆装结构 - Google Patents

旋翼飞行器及电机散热结构、机臂与机身的连接结构和脚架拆装结构 Download PDF

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Publication number
WO2016066009A1
WO2016066009A1 PCT/CN2015/091753 CN2015091753W WO2016066009A1 WO 2016066009 A1 WO2016066009 A1 WO 2016066009A1 CN 2015091753 W CN2015091753 W CN 2015091753W WO 2016066009 A1 WO2016066009 A1 WO 2016066009A1
Authority
WO
WIPO (PCT)
Prior art keywords
arm
rotorcraft
motor
top cover
sleeve
Prior art date
Application number
PCT/CN2015/091753
Other languages
English (en)
French (fr)
Inventor
彭斌
肖锭锋
Original Assignee
广州极飞电子科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from CN201420631048.8U external-priority patent/CN204223176U/zh
Priority claimed from CN201420631071.7U external-priority patent/CN204223174U/zh
Priority claimed from CN201420626211.1U external-priority patent/CN204223187U/zh
Application filed by 广州极飞电子科技有限公司 filed Critical 广州极飞电子科技有限公司
Priority to ES15855700T priority Critical patent/ES2728409T3/es
Priority to PL15855700T priority patent/PL3213995T3/pl
Priority to AU2015341237A priority patent/AU2015341237B2/en
Priority to EP15855700.9A priority patent/EP3213995B1/en
Priority to EP17167044.1A priority patent/EP3246251B1/en
Priority to EP17167048.2A priority patent/EP3239044B1/en
Publication of WO2016066009A1 publication Critical patent/WO2016066009A1/zh
Priority to US15/484,183 priority patent/US11358709B2/en
Priority to US15/484,194 priority patent/US10611469B2/en
Priority to US15/484,395 priority patent/US10501171B2/en
Priority to AU2017203554A priority patent/AU2017203554B2/en
Priority to AU2017203550A priority patent/AU2017203550B2/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B64C1/069—Joining arrangements therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/52—Skis or runners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/58—Arrangements or adaptations of shock-absorbers or springs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/90—Cooling
    • B64U20/94—Cooling of rotors or rotor motors
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K9/00—Arrangements for cooling or ventilating
    • H02K9/02—Arrangements for cooling or ventilating by ambient air flowing through the machine
    • H02K9/04—Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium
    • H02K9/06—Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface  specially adapted for helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors

Definitions

  • the present invention relates to the field of aircraft technology, and in particular to a rotorcraft, a rotor heat dissipating structure of a rotorcraft, a connecting structure of a rotorcraft arm and a fuselage, and a tripod assembly and disassembly of the rotorcraft structure.
  • a rotorcraft also known as a rotorcraft, typically includes a fuselage, an arm, and a propeller, one end of which is coupled to the fuselage and the propeller is mounted to the other end of the arm.
  • one end of the propeller is mounted with a motor, which is usually placed in a closed housing at the end of the arm.
  • a motor which is usually placed in a closed housing at the end of the arm.
  • the arm and the fuselage of the conventional rotorcraft are connected by integral molding.
  • the motor, the connecting line of the motor and the control line of the propeller are required because the position of the propeller is required to be installed at the outer end of the arm. It is necessary to pass through the inside of the arm through the electronic components such as the circuit board and the controller connected to the fuselage, which requires the arm to be set as a hollow structure. Therefore, the structure in which the arm and the body are integrally formed is difficult to process, and Once the fall occurs, once the arm is bent, the fuselage and other arms are scrapped at the same time.
  • a tripod In order to support the rotorcraft and to reduce the shock when landing, a tripod is usually installed under the fuselage of the rotorcraft. When taking off, the tripod will support the fuselage so that the propeller on the fuselage is at a certain height from the ground. When the spiral will rotate, the generated airflow can cause the fuselage to rise against gravity. When landing, the tripod contacts the ground and acts as a shock absorber to cushion the damage of the fuselage.
  • the current tripod of the rotorcraft is usually fixed to the fuselage by bolts. The installation and disassembly process is cumbersome, and the quick disassembly and installation of the tripod cannot be realized, which is not conducive to the maintenance and replacement of the tripod.
  • the present invention aims to solve at least one of the technical problems in the related art to some extent.
  • the present invention needs to provide a motor heat dissipation structure of a rotorcraft, which can effectively reduce the temperature of the working environment of the motor.
  • the motor heat dissipation structure of the rotorcraft includes: a casing fixed to an end of the rotorcraft arm, the casing is a hollow structure having a top opening and a bottom air inlet, and the motor body is fixedly mounted inside the casing, and the periphery of the motor body Forming an air flow path with the inner wall of the outer casing; a top cover synchronously coupled to the rotating shaft of the motor, the top cover is capped over the top opening, and an air flow path is formed between the lower surface of the peripheral edge of the top cover and the top end surface of the outer casing A gap communicating with the outside, the lower surface of the top cover is provided with a plurality of air flow picks; and a mounting seat fixed on the upper surface of the top cover for connecting with the propeller of the rotorcraft.
  • a plurality of air flow picks are circumferentially arranged around the central axis of the top cover, the air flow picking direction is extended to be consistent with the radial direction of the top cover, the air flow picking piece is triangular, and the distance between the top end surface and the bottom end surface of the air flow picking piece It gradually decreases from the inside to the outside.
  • the upper surface of the top cover forms a water guiding surface, the height of the water guiding surface gradually decreases from the middle to the edge; the edge of the top cover is located outside the top edge of the outer casing.
  • a bracket is fixed on the rotating shaft of the motor, and the top cover and the mounting seat are fixed to the bracket by bolts.
  • the invention utilizes external air to perform continuous air cooling on the motor, ensures that the motor is always working in a low temperature environment, improves the stability and reliability of the motor, and prolongs the service life of the motor. Effectively prevent rainwater from entering the inside of the enclosure and ensure that the motor works properly.
  • the present invention also needs to provide a connection structure between the arm of the rotorcraft and the fuselage, which not only can realize quick disassembly and installation of the arm and the fuselage, but also has strong waterproofness.
  • the connecting structure of the arm of the rotorcraft and the fuselage includes a fuselage and an arm, wherein a fixed sleeve protrudes from a periphery of the fuselage, and a first external thread is disposed outside the fixed sleeve, and the front end of the arm
  • the insertion head is inserted into the fixed sleeve, and the insertion head is provided with a protrusion protruding from the outer surface of the arm, and a protruding groove is formed between the protrusion and the outer surface of the arm, and the protrusion is formed
  • the front end forms a mating surface;
  • the arm is sleeved with a lock nut and a lock sleeve, the lock nut is screwed to the first external thread, and the rear end thereof has a tension end abutting against the rear end surface of the boss portion, and is fixed
  • a first sealing ring is sandwiched between the outer end surface of the sleeve and the mat
  • the insertion head is detachably sleeved on the front end of the arm.
  • a female plug is disposed in the fixed sleeve, and a male plug inserted in the female plug is disposed in the insertion head.
  • the insertion head is provided with a radially outwardly extending extension, the projection extending rearward from the edge of the extension, and the mating surface is the front end surface of the extension.
  • the surface of the insertion head is provided with an axially extending groove
  • the inner wall of the fixing sleeve is provided with a boss embedded in the groove
  • the invention locks the arm and the fuselage by the lock nut and the lock sleeve, thereby realizing quick installation and disassembly of the fuselage and the arm, and at the same time, pressing the seal ring by means of thread locking , to make the fuselage and arm joints have a strong waterproof seal.
  • the present invention also needs to propose a tripod dismounting structure of a rotorcraft, which can realize rapid installation and disassembly of the tripod and the rotorcraft fuselage.
  • the tripod dismounting structure of the rotorcraft includes: a receiving slot disposed on a bottom wall of the rotorcraft fuselage and having an opening facing downward; a jack is formed on a top wall of the receiving slot, and one of the side walls of the receiving slot is disposed a fixing slot is fixedly mounted on the tripod and received in the receiving slot, the mounting seat is fixed with an insert inserted in the card slot; and the movable latch is mounted in the fixing seat, a portion of the latch that is formed by the upper surface of the mounting seat to form a mating insertion hole in the insertion receptacle; an elastic member for providing a pressing pin for embedding the plug end in the receptacle; Pressing the pin to push the pin toward the direction away from the jack.
  • a latch is disposed on the latch, and the inner side of the push rod is sleeved on the latch and located above the flap.
  • a connecting seat is fixed in the tripod, and the elastic member is defined between the connecting seat and the blocking piece, and the fixing seat is screwed on the connecting seat.
  • the fixing seat is provided with a limiting slot for limiting the up and down movement of the push rod.
  • the fixing seat is provided with a fixing groove
  • the inserting member is a card fixed in the fixing groove and extending from the fixing groove.
  • the invention can realize the quick disassembly and installation of the tripod and the fuselage, simplifies the assembly process of the rotorcraft, and can facilitate the replacement and maintenance of the rotorcraft components.
  • FIG. 1 is a complete machine diagram of a rotorcraft according to an embodiment of the present invention.
  • FIG. 2 is an exploded view of a heat dissipation structure of a rotor of a rotorcraft according to an embodiment of the present invention
  • Figure 3 is a cross-sectional view of the heat dissipation structure of the motor shown in Figure 2;
  • FIG. 4 is a schematic structural view of a top cover in the heat dissipation structure of the motor shown in FIG. 2;
  • FIG. 5 is a schematic view showing a connection structure of a boom and a fuselage of a rotorcraft according to an embodiment of the present invention
  • Figure 6 is a cross-sectional view of the arm in the connection structure of the arm and the body shown in Figure 5;
  • Figure 7 is an enlarged view of the area A in Figure 6;
  • FIG. 8 is a schematic structural view of a tripod dismounting structure of a rotorcraft according to an embodiment of the present invention.
  • Figure 9 is a schematic structural view of the stand of the tripod dismounting structure of Figure 8.
  • FIG. 10 is a schematic structural view of the stand of the tripod dismounting structure of FIG. 8.
  • FIG. 10 is a schematic structural view of the stand of the tripod dismounting structure of FIG. 8.
  • Body 100 fixed sleeve 11; first external thread 111; boss 112; receiving groove 12; top wall 121;
  • Motor heat dissipation structure 400 outer casing 410; air inlet 411; air flow passage 412; top cover 430; air flow pick 431; water guide surface 432; bracket 440;
  • Tripod 500 fixing base 51; fixing groove 511; limiting groove 512; inserting member 52; latch 53; blocking piece 531; push rod 54; elastic member 55; connecting seat 56;
  • connection should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or through the middle.
  • the medium is indirectly connected, and may be a communication inside two elements or an interaction relationship of two elements.
  • the first feature "on” or “under” the second feature may include direct contact of the first and second features, and may also include first and second features, unless otherwise specifically defined and defined. It is not in direct contact but through additional features between them.
  • the first feature "above”, “above” and “above” the second feature includes the first feature directly above and above the second feature, or merely indicating that the first feature level is higher than the second feature.
  • the first feature “below”, “below” and “below” the second feature includes the first feature directly below and below the second feature, or merely the first feature level being less than the second feature.
  • a rotorcraft 1000 in accordance with an embodiment of the present invention includes a fuselage 100, a boom 200, and a propeller 300.
  • the bottom of the fuselage 100 may be provided with a tripod 500, which supports the fuselage 100 and acts as a shock absorber when the rotorcraft 1000 is lowered.
  • the stand 500 may include a plurality of symmetrically disposed at the bottom of the body 100.
  • the stand 500 is also one and disposed at the center of the bottom of the body 100.
  • the first end 201 (mounting end, root, front end) of the arm 200 is connected to the body 100, as shown in FIG. 1 .
  • the arm 200 may be multiple, for example, Four, or eight or more.
  • the plurality of arms 200 are symmetrically arranged with respect to the body 100.
  • a propeller 300 is disposed on the second end 202 (free end, end, rear end) of each arm 200, and the propeller 300 is horizontally disposed on the corresponding arm 200.
  • the propeller 300 is driven to rotate by the motor 600.
  • the number of the motors 600 may be plural, and the number of the motors 600 may be the same as the number of the propellers 300, that is, each of the propellers 300 is driven to rotate by one motor 600.
  • the mounting position of the motor 600 corresponds to the position of the propeller 300, that is, the motor 600 may also be disposed at the second end 202 of the corresponding arm 200.
  • the rotorcraft 1000 further includes a motor heat dissipation structure 400, a connection structure of the arm 200 and the body 100, and a quick disassembly structure of the stand 500. Specific embodiments of the above respective structures will be described in detail below.
  • a motor heat dissipation structure 400 of a rotorcraft 1000 in accordance with an embodiment of the present invention will now be described with reference to Figs.
  • the motor heat dissipation structure 400 of the rotorcraft 1000 according to an embodiment of the present invention includes a housing 410, a top cover 430, and a mount 450.
  • the outer casing 410 is disposed on the second end 202 of the arm 200.
  • the outer casing 410 is a hollow structure having a top opening and a bottom air inlet 411, and the body of the motor 600 is disposed inside the outer casing 410, wherein, optionally, The body of the motor 600 can be fixedly mounted relative to the outer casing 410, that is, in normal use, the motor 600 is stationary relative to the outer casing 410, thereby making the drive of the motor 600 more stable to the propeller 300.
  • the body of the motor 600 is detachably mounted relative to the outer casing 410, thereby facilitating replacement and maintenance of the motor 600.
  • the rotating shaft of the motor 600 protrudes from the outer casing 410, and an air flow passage 412 is formed between the circumference of the body of the motor 600 and the inner wall of the outer casing 410.
  • the air inlet 411 may be a small hole disposed at the bottom of the side wall of the outer casing 410.
  • the number of the small holes may be multiple.
  • the shape of the small hole may be any, for example, may be a circle. Any of an oblong shape, a polygonal shape, or an irregular shape may be sufficient as long as external air can enter the air flow path 412 from the air inlet 411 into the outer casing 410.
  • the top opening of the outer casing 410 may be formed by the upper end of the outer casing 410 being entirely open, or the top of the air flow path 412 in the outer casing 410 may be open.
  • the top cover 430 is synchronously connected to the rotating shaft of the motor 600.
  • the top cover 430 is capped over the top opening.
  • a gap between the lower surface of the top cover 430 and the top end surface of the outer casing 410 is formed to communicate the air flow passage 412 with the outside.
  • the gap is formed between the lower surface of the periphery of the top cover 430 and the top end surface of the outer casing 410, thereby making the motor heat dissipation structure 400 more reasonable and facilitating gas circulation.
  • the air inlet 411, the air flow path 412, and the gap form a circuit that communicates with the external environment, and the lower surface of the top cover 430 is provided with a plurality of air flow picks 431.
  • the mounting seat 450 is fixed on the upper surface of the top cover 430 and is used for connecting with the propeller 300.
  • the mounting seat 450 and the propeller 300 can be installed by any form, such as a screw connection, a snap connection, a welded connection, etc. This fixes the propeller 300 to the mount 450, and the motor 600 drives the top cover 430 to rotate, so that the top cover 430 can drive the propeller 300 to rotate.
  • the outer casing 410 is fixed to the end of the rotor 200 of the rotorcraft 1000, and the outer casing 410 is a hollow structure having a top opening and a bottom air inlet 411.
  • the air inlet 411 may be a small hole disposed at the bottom of the side wall of the outer casing 410, and the small hole
  • the number of the motor 600 may be installed inside the outer casing 410.
  • An air flow passage 412 is formed between the circumference of the motor 600 and the inner wall of the outer casing 410.
  • the top cover 430 is synchronized on the rotating shaft of the motor 600, and the top is The cover 430 is located above the outer casing 410, that is, over the top opening, and a gap is formed between the lower surface of the periphery of the top cover 430 and the top end surface of the outer casing 410, and the gap connects the upper end portion of the air flow passage 412 to the outside. Therefore, the air inlet 411, the air flow path 412, and the gap form a circuit that communicates with the external environment, and the lower surface of the top cover 430 is provided with a plurality of air flow picks 431; the mounting base 450 is fixed to the top cover 430.
  • the surface may be provided with external threads on the mount 450 for securing the propeller 300 to the mount 450 such that the shaft of the motor 600 drives the propeller 300 to rotate.
  • the rotating shaft drives the top cover 430 to rotate, and the air flow picking piece 431 disposed on the lower surface of the top cover 430 moves the air flowing inside the outer casing 410, and under the action of the centrifugal force, a negative pressure is formed on the top of the outer casing 410, and the airflow is
  • the air flow passage 412 flows from bottom to top, and the lower temperature air in the external environment enters the air flow passage 412 from the air inlet 411.
  • the lower temperature air exchanges heat with the body of the motor 600 to carry the heat away.
  • the gap between the top cover 430 and the top end surface of the outer casing 410 flows out, so that the air circulation is continuously formed, so that the air of the motor 600 is cooled by the outside air, so that the motor 600 is always operated in a low temperature environment, thereby improving the motor 600.
  • the stability and reliability of the motor 600 extend the service life of the motor 600.
  • the plurality of air flow picks 431 may be circumferentially arranged around the central axis of the top cover 430, and the air flow picking 431 may extend in a direction consistent with the radial direction of the top cover 430.
  • each air flow paddle 431 may have a triangular shape, and the distance between the top end face and the bottom end face of the air flow paddle 431 gradually decreases from the inside to the outside.
  • the distribution of the plurality of air flow picks 431 may be set to a spiral shape as needed, and the air flow picking 431 may extend in an angle with the radial direction of the top cover 430.
  • the air flow paddle 431 can move the airflow inside the outer casing 410 outward, at the top of the outer casing 410. A negative pressure can be generated.
  • each air flow paddle 431 the end of the air flow paddle 431 adjacent to the center of the top cover 430
  • the inner end of each air flow pick 431 surrounds a recessed area in the middle of the top cover 430, and when the top cover 430 rotates with the rotation axis of the motor 600, a negative pressure can be formed at the area.
  • the air pressure to be sucked is lower than the air pressure at the gap between the inner wall of the outer casing 410 and the motor 600, so that the hot air inside the motor enters the negative pressure region surrounded by the inner end of the air flow dial 431 under the influence of the air pressure difference, and then The air flow passage 412 is discharged at a high speed to function as a heat sink of the motor.
  • the upper surface of the top cover 430 may form a water guiding surface 432.
  • the height of the water guiding surface 432 is gradually decreased from the middle to the edge, and the diameter of the top cover 430 is larger than the diameter of the top of the outer casing 410, that is, the top cover 430.
  • the edge is located outside the top edge of the outer casing 410, so that the rainwater flows down the water guiding surface 432, and does not enter the inside of the outer casing 410 from the gap formed between the top cover 430 and the top end surface of the outer casing 410, thereby achieving waterproofing. purpose.
  • a bracket 440 is fixed to the rotating shaft of the motor 600.
  • the top cover 430 and the mounting base 450 can be fixed to the bracket 440 by bolts, which can facilitate the installation and replacement of the motor 600.
  • the present invention utilizes external air to perform continuous air cooling on the motor 600, ensures that the motor 600 is always operated in a low temperature environment, improves the stability and reliability of the motor 600, and prolongs the service life of the motor 600. At the same time, it can effectively prevent rainwater from entering the inside of the outer casing 410, and ensure that the motor 600 works normally.
  • connection structure of the arm 200 of the rotorcraft 1000 to the body 100 will be described below with reference to FIGS. 1 and 5-7.
  • the rotorcraft 1000 includes four arms 200, which will be described below with the rotorcraft 1000 having four arms 200 as an example.
  • the connecting structure of the arm 200 of the rotorcraft 1000 and the body 100 includes a fixing sleeve 11, a insertion head 23, a lock sleeve 22, and a lock nut 21.
  • the fixing sleeve 11 protrudes from the periphery of the body 100, and the periphery of the body 100 protrudes from the four fixing sleeves 11, and the four arms 200 respectively cooperate with the four fixing sleeves 11. installation.
  • the insertion head 23 is disposed at the first end 201 of the arm 200 (one end and the front end of the arm 200 adjacent to the body 100), and the insertion head 23 is used for inserting the fixed sleeve. 11 , specifically, the insertion head 23 is sleeved at the first end 201 of the arm 200 in the direction from the first end 201 of the arm 200 to the second end, that is, as shown in FIGS. 5 and 6 It is shown that the insertion head 23 is fitted to the first end 201 of the arm 200 from the front to the rear.
  • the insertion head 23 is provided with a convex portion 232 protruding from the outer surface of the arm 200, and an insertion groove is formed between the convex portion 232 and the outer surface of the arm 200, as shown in FIG. 5 and FIG. 232 may be located at the second end of the insertion head 23, that is, the convex portion 232 is located at the rear end of the insertion head 23, and the convex portion 232 has a gap with the outer surface of the arm 200, and the gap is formed as a cartridge.
  • the groove as seen from Fig. 5 and Fig. 6, the opening of the insertion groove faces rearward.
  • the locking sleeve 22 is sleeved on the arm 200.
  • the locking sleeve 22 has an insertion portion 221 embedded in the insertion slot. Specifically, as shown in FIG. 5 and FIG. 6, the insertion portion 221 is located at the front end of the locking sleeve 22 and Inserted into the insertion slot before.
  • the insertion head 23 is detachably sleeved on the first end 201 of the arm 200.
  • the insertion head 23 may be screwed to the first end 201 of the arm 200, or inserted.
  • the head 23 can also be coupled to the first end 201 of the arm 200 by a snap-fit structure.
  • the insertion portion 221 and the boss portion 232 can be screwed, whereby the screwing connection can facilitate the installation between the insertion portion 221 and the boss portion 232, thereby facilitating the installation of the insertion head 23 and the lock sleeve 22, and
  • the connection is stable.
  • the degree of tightness of the insertion head 23 and the lock sleeve 22 can be adjusted as needed.
  • the lock nut 21 is sleeved on the arm 200, and the second end (rear end) of the lock nut 21 has a tension end that abuts against the second end face (rear end face) of the boss portion 232.
  • the lock nut 21 is screwed to the fixed sleeve 11, whereby when the insertion head 23 is stably mounted on the arm 200, the position of the boss 232 is fixed, and when the lock nut 21 and the fixed sleeve 11 are tightened
  • the boss portion 232 acts as a tension on the lock nut 21, the position of the lock nut 21 is ensured, thereby ensuring the fastening between the fixed sleeve 11 and the lock nut 21, and the sleeve 11 is fixed.
  • the threaded connection is made between the lock nut 21 and the lock nut 21, so that the assembly can be facilitated, and the tightness between the fixed sleeve 11 and the lock nut 21 can be adjusted as needed.
  • the outer surface of the fixing sleeve 11 is provided with a first external thread 111, and the lock nut 21 is screwed onto the first external thread 111, thereby achieving the lock nut 21 and the fixed sleeve 11
  • the purpose of the threaded connection is provided.
  • the outer surface of the insertion portion 221 is provided with a second external thread 222 screwed to the inner surface of the convex portion 232, whereby the purpose of screwing between the insertion portion 221 and the convex portion 232 can be achieved.
  • the first end (front end) of the convex portion 232 is formed with a mating surface 231, which is solid.
  • the first sealing ring 24 is sandwiched between the outer end surface (free end surface) of the sleeve 11 and the mating surface 231.
  • the first sealing ring 24 is sleeved on the outer surface of the insertion head 23, thereby ensuring The insertion head 23 is locked with the fixing sleeve 11.
  • the insertion head 23 is provided with a radially outwardly extending extending portion 234.
  • the protruding portion 232 is formed by extending the edge of the extending portion 234 toward the second end 202 of the arm 200, and the mating surface 231 is an extension portion.
  • the lock sleeve 22 is sleeved with a second seal ring 25, and the second seal ring 25 is clamped between the outer surface of the lock sleeve 22 and the inner surface of the second end portion (rear end portion) of the lock nut 21.
  • the second sealing ring 25 can provide a certain pre-tightening force for the lock nut 21, ensuring the firmness of the connection of the lock nut 21 to the fixed sleeve 11.
  • the body 100 is provided with a fixing sleeve 11
  • the arm 200 is provided with an insertion head 23 , a lock nut 21 and a lock sleeve 22
  • the fixing sleeve 11 is The outer periphery of the body 100 extends, and the outer surface is provided with a first external thread 111.
  • the fixing sleeve 11 can be detachably fixed inside the body 100.
  • the body 100 is disposed as an upper and lower casing.
  • the fixing sleeve 11 is pre-buried in the semi-circular groove of the lower casing, and the limiting structure is used to define the degree of freedom of the fixing sleeve 11 along its own axial direction, and then the upper casing is fastened to fix the upper casing and the lower casing.
  • the fixing sleeve 11 is fixed to the body 100.
  • the fixing sleeve 11 and the body 100 can be fixed by other structures, which are generally well known to those skilled in the art and will not be described in detail herein.
  • the insertion head 23 is disposed at the front end of the arm 200 in a socket fit manner, and the insertion head 23 has a protrusion 232 protruding from the outer surface of the arm 200, the protrusion 232 and the outer surface of the arm 200.
  • An insertion slot is formed between the insertion head 23 and a radially outwardly extending portion 234 extending from the extension portion 234. The front end surface of the extension portion 234 is formed.
  • a radial mating surface 231 the mating surface 231 mates with the end surface of the fixing sleeve 11, a first sealing ring 24 between the mating surface 231 and the end surface of the fixing sleeve 11 is sleeved outside the inserting head 23;
  • the lock nut 21 and the lock sleeve 22 are respectively sleeved on the arm 200.
  • the lock nut 21 is screwed to the first external thread 111, and the rear end portion abuts against the tension end of the rear end surface of the boss portion 232, and is tightened.
  • the tightening end of the lock nut 21 can push the insertion head 23 toward the fixing sleeve 11 to fully clamp the first sealing ring 24 with the mating surface 231 and the end surface of the fixing sleeve 11;
  • the sleeve 22 has an insertion portion 221 embedded in the insertion groove, and the outer surface of the insertion portion 221 is provided with a second external thread 222.
  • the second external thread 222 should be provided with an internal thread 233 on the inner surface of the boss 232.
  • a second sealing ring 25 is sleeved on the locking sleeve 22, and the second sealing ring 25 is clamped in the locking sleeve.
  • the outer surface of 22 is between the inner surface of the rear end of the lock nut 21.
  • the surface of the arm 200 extends outwardly with a flange 26 that is clamped between the extension 234 and the front end face of the insertion portion 221.
  • the lock sleeve 22, the lock nut 21 and the insertion head 23 are sequentially placed on the front end of the arm 200, and then the insertion head 23 is inserted into the fixed sleeve 11, and the lock sleeve 22 is screwed, using the second The external thread 222 and the internal thread 233 lock the insertion head 23 and the lock sleeve 22, that is, the flange 26 is clamped between the extension portion 234 and the insertion portion 221, and then the lock nut 21 is tightened, so that The mating surface 231 and the end surface of the fixing sleeve 11 fully clamp the first sealing ring 24 to ensure that the insertion head 23 and the fixing sleeve 11 are locked.
  • a connecting member for the circuit conduction is provided in the fixing sleeve 11 and the insertion head 23, respectively.
  • the connecting member in the fixing sleeve 11 and the connecting member in the insertion head 23 are in contact with each other, so that the circuit can be turned on.
  • the circuit may be the power supply circuit and/or the control circuit of the motor 600 and the propeller 300. This makes it easy to connect and conduct the circuit.
  • the structure of the connecting member in the fixing sleeve 11 and the insertion head 23 may be arbitrary as long as the two are in contact with each other to ensure the conduction of the circuit.
  • the fixing sleeve 11 and the insertion head 23 may respectively be provided with metal sheets, and the two metal sheets are in contact with each other to satisfy the purpose of circuit conduction.
  • a female plug is disposed in the fixed sleeve 11, and a male plug inserted into the female plug is disposed in the insertion head 23 to ensure electrical conduction of the electrical components, and can be quickly and accurately docked.
  • the outer surface of the insertion head 23 is provided with an axially extending groove 235, and the inner wall of the fixed sleeve 11 is provided with a boss 112 embedded in the groove 235.
  • an axially extending groove 235 is disposed on the surface of the insertion head 23, and the inner wall of the fixing sleeve 11 is provided with a boss 112 embedded in the groove 235, and the boss is inserted during insertion.
  • the 112 is embedded in the recess 235, whereby not only the mounting of the arm 200 and the fixed sleeve 11 can be guided.
  • grooves 235 at different positions may be disposed on the insertion head 23 on each arm 200 of the rotorcraft 1000, and a boss 112 corresponding to the position of the groove 235 is disposed on the fixed sleeve 11 corresponding to the arm 200, It can be ensured that the arm 200 can be correctly mounted on the corresponding fixed sleeve 11, thereby quickly identifying the mounting position of the different arms 200 to ensure that the rotorcraft 1000 can operate normally.
  • the present invention locks and fixes the arm 200 and the body 100 by the lock nut 21 and the lock sleeve 22, thereby realizing quick installation and disassembly of the body 100 and the arm 200, and simultaneously locking with the thread.
  • the method of pressing the sealing ring has a strong waterproof sealing joint between the fuselage 100 and the arm 200.
  • the rotorcraft 1000 includes two tripods 500 that are symmetrically disposed at the bottom of the fuselage 100 with respect to a centerline of the fuselage 100.
  • Each of the legs 500 and the body 100 has two connecting ends.
  • the connecting end of each of the legs 500 has a quick dismounting structure of the stand 500 of the embodiment of the present invention.
  • the quick release structure of the stand 500 of the rotorcraft 1000 includes: a receiving groove 12 disposed on the bottom wall of the body 100 and having a downward opening, and a fixing seat 51.
  • the top wall 121 of the accommodating groove 12 is provided with a socket 122.
  • the fixing base 51 is fixedly connected to the pedestal 500 and received in the accommodating groove 12, and the latch 53 is movably mounted on the fixing base 51.
  • the latch 53 is movable in the up and down direction, and a portion through which the latch 53 passes out from the upper surface of the mount 51 is formed with a plug end, and the plug end is fitted into the insertion hole 122.
  • the side wall of the accommodating groove 12 is provided with a card slot 123.
  • the fixing seat 51 is further provided with an inserting member 52.
  • the inserting member 52 fits in the card slot 123, so that the current inserting member 52 fits between After the insertion of the pin 53 into the insertion hole 122, the fixing base 51 can be fixed in the accommodating groove 12, thereby serving the purpose of providing the stand 500 on the body 100.
  • the elastic member 55 is for providing a pressing force of the pressing pin 53 to embed the plug end in the insertion hole 122, that is, the elastic member 55 is configured in a normally compressed state, whereby the plug 53 can be pressed.
  • the push rod 54 When the push rod 54 is pressed, the pin 53 is moved toward the direction away from the insertion hole 122, so that when the tripod 500 needs to be disassembled, the push rod 54 can be pressed, so that the pin 53 is disengaged from the insertion hole 122, and then the insertion is performed.
  • the mounting member 52 pivots the fixing base 51 downwardly, thereby disengaging the inserting member 52 from the card slot 123, thereby quickly disassembling the stand 500 from the body 100.
  • the mounting member 52 is inserted into the card slot 123 and the fixing base 51 is pushed upward by the inserting member 52.
  • the elastic member 55 is present.
  • the plug end is embedded in the jack 122, thereby completing the installation.
  • the fixing base 51 is provided with a fixing groove 511
  • the inserting member 52 is a card positioned in the fixing groove 511 and extending from the fixing groove 511.
  • the fixing seat 51 is provided with a limiting groove 512 for limiting the up and down movement of the push rod 54, thereby limiting and positioning the movement of the push rod 54.
  • the latch 53 is optionally provided with a blocking piece 531.
  • the push rod 54 is sleeved on the latch 53 and located above the blocking piece 531, so that the latch 53 can be pushed downward by the push rod 54 to move. The role.
  • the rotorcraft 1000 tripod 500 quick-disassembling structure is an accommodating groove 12 having an opening downward facing the bottom wall of the body 100, and a fixing seat 51 is fixedly coupled to the top end of the stand 500.
  • a socket 122 is defined in the top wall 121 of the accommodating slot 12, and a slot 123 is defined in one of the sidewalls of the accommodating slot 12;
  • the shape of the fixing base 51 is the same as the shape of the accommodating slot 12, and the fixing
  • the seat 51 is received in the accommodating groove 12, and a card is disposed on one side of the fixing base 51. After the fixing base 51 is received in the accommodating groove 12, the card is inserted into the card slot 123; the fixing base 51 is a hollow structure.
  • the inner portion is provided with a latch 53 which can move up and down.
  • the extending direction of the latch 53 coincides with the height direction.
  • the upper end portion of the latch 53 is pierced by the upper surface of the fixing base 51, and the through portion forms a matching insertion into the insertion hole 122.
  • the inner end of the plug end; the latch 53 is sleeved with a spring for providing a spring stress for pushing the pin 53 upward to insert the plug end of the top of the pin 53 into the jack 122.
  • the spring can Is jammed at the bottom of the mount 51 and inserted Between 53, it may be stuck between the stand 500 and the pin 53.
  • a blocking piece for the upper end of the pressing spring can be arranged on the bolt 53 531, that is, the spring is defined between the flap 531 and the bottom of the fixed seat 51, or the spring is defined between the flap 531 and the stand 500; it should be noted here that the spring provides the push pin 53.
  • Elastic stress which may also be other elastic component parts, such as elastic rubber blocks and the like.
  • a push rod 54 is further connected to the latch 53.
  • the push rod 54 When the push rod 54 is pressed down, the push rod 54 drives the latch 53 to move downward, so that the plug end of the top of the latch 53 can be disengaged from the jack 122.
  • the push rod 54 The inner end of the push rod 53 is disposed on the latch 53 and is located above the retaining block 51.
  • the outer end of the push rod 54 extends through the limiting slot 512 formed in the fixing base 51 to the outside of the fixing base 51 for easy operation. It is used to define the formation of the up and down movement of the push rod 54 and to guide the up and down movement of the push rod 54.
  • the disassembling structure of the present invention When the disassembling structure of the present invention is disassembled, the outer end of the push rod 54 is pushed downward, the push rod 54 drives the latch 53 to move downward, and the plug end of the top of the latch 53 is disengaged from the jack 122.
  • the tripod 500 is rotated with the card as a fulcrum.
  • the plug end of the top of the latch 53 is just inserted into the jack 122, and the spring is elastic. Under the action of the stress, the latch 53 does not disengage from the receptacle 122, thereby securing the stand 500 below the fuselage 100.
  • the card may be integrally formed with the fixing base 51, or may be separately formed. Specifically, a fixing groove 511 is defined in the fixing base 51, and the card is fixed in the fixing groove 511 and protrudes from the fixing groove 511. It may be an aluminum sheet or other inserts 52 that can be embedded inside the card slot 123.
  • a connecting seat 56 is fixed in the tripod 500.
  • the spring is defined between the connecting seat 56 and the blocking piece 531.
  • the outer periphery of the connecting seat 56 is provided with an external thread, and the fixing seat 51 is internally provided with an internal thread matched with the external thread, thereby The fixing base 51 is screwed onto the stand 500.
  • the present invention can realize the quick disassembly and installation of the tripod 500 and the fuselage 100, simplifies the assembly process of the rotorcraft 1000, and can facilitate the replacement and maintenance of the components of the rotorcraft 1000.

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Abstract

一种旋翼飞行器（1000），该旋翼飞行器（1000）包括：机身（100）；机臂（200），机臂（200）的第一端（201）连接在机身（100）上；螺旋桨（300），螺旋桨（300）连接在机臂（200）的第二端（202），螺旋桨（300）由电机（600）驱动旋转；电机散热结构（400），包括：外壳（410），外壳（410）为具有顶部开口和底部进风口（411）的空心结构，电机（600）的机体设在外壳（410）的内部，电机（600）的机体的周缘与外壳（410）的内壁之间形成有空气流道（412）；顶盖（430），顶盖（430）同步连接于电机（600）的转轴上，顶盖（430）的下表面设置有多个气流拨片（431）；安装座（450），安装座（450）固定在顶盖（430）上表面且用于与螺旋桨（300）连接。另外，还披露了一种旋翼飞行器的电机散热结构、机臂与机身的连接结构和脚架拆装结构。该旋翼飞行器的电机工作环境温度有效降低，机臂与机身可以快速拆卸和安装，简化了旋翼飞行器的组装过程。

Description

旋翼飞行器及电机散热结构、机臂与机身的连接结构和脚架拆装结构 技术领域
本发明涉及飞行器技术领域，具体而言，涉及一种旋翼飞行器，一种旋翼飞行器的电机散热结构、一种旋翼飞行器的机臂与机身的连接结构，以及一种旋翼飞行器的脚架拆装结构。
背景技术
旋翼飞行器也被称之为旋翼直升机，其通常包括机身、机臂、以及螺旋桨，机臂的一端连接机身，螺旋桨安装在机臂的另一端。
为了驱动螺旋桨高速转动，在机臂上安装螺旋桨的一端还设置有电机，电机通常是被置于机臂端部的封闭壳体内。目前的旋翼飞行器在工作时，由于电机带动螺旋桨高速转动，电机大负荷运行时，其机体产生较大的热量，这些热量很难在封闭的壳体内部及时被散出，因此，电机长时间在高温的封闭空间内运行，其稳定性以及可靠性较差，甚至会发生停机，从而导致旋翼飞行器坠落。
传统的旋翼飞行器的机臂与机身是通过一体成型的方式连接的，这种结构虽然简单，但是，由于需要在机臂外侧端安装螺旋桨的位置设置电机，电机的连接线以及螺旋桨的控制线需要从机臂内部穿过连接至机身的电路板、控制器等电子元件，这就要求机臂需要设置为空心结构，因此，机臂与机身一体成型的结构加工难度较大，并且在发生坠落后，机臂一旦被折弯，机身与其他的机臂均同时报废。为了改善上述缺陷，也有一些旋翼飞行器的机臂与机身是采用扣接的方式进行固定，将空心管状的机臂穿入到机身中，利用具有弹性的卡扣将机臂与机身固定，其虽然能够实现机臂的快速拆卸和安装，但是，这种结构的防水性较差。
为了对旋翼飞行器进行支撑以及降落时起到减震作用，通常在旋翼飞行器的机身下方安装脚架，在起飞时，脚架将支撑机身，使机身上的螺旋桨距离地面一定高度，从而在螺旋将旋转时，产生的气流能够使机身克服重力升起，降落时，脚架接触地面，起到减震的作用以缓冲机身的损伤。目前的旋翼飞行器的脚架通常是通过螺栓固定在机身上，其安装和拆卸过程较为繁琐，不能够实现脚架的快速拆卸和安装，不利于脚架的维修和更换。
发明内容
本发明旨在至少在一定程度上解决相关技术中的技术问题之一。
针对现有技术的不足，本发明需要提出一种旋翼飞行器的电机散热结构，其能够有效的降低电机工作环境的温度。
所述旋翼飞行器的电机散热结构包括：固定于旋翼飞行器机臂端部的外壳，该外壳为一具有顶部开口和底部进风口的空心结构，电机的机体固定安装在该外壳内部，电机机体的周缘与外壳的内壁之间形成空气流道；同步联接于电机转轴上的顶盖，该顶盖封盖于顶部开口的上方，顶盖的周缘下表面与外壳的顶端面之间形成将空气流道与外界连通的间隙，顶盖的下表面设置有多个气流拨片；固定在顶盖上表面用于与旋翼飞行器的螺旋桨连接的安装座。
可选地，多个气流拨片绕顶盖的中心轴线圆周阵列，气流拨片的延伸方向与顶盖的径向一致，气流拨片呈三角形且气流拨片顶端面和底端面之间的距离由内向外逐渐减小。
可选地，顶盖的上表面形成一导水面，该导水面的高度由中间向边缘逐渐降低；顶盖的边缘位于外壳顶部边缘的外侧。
可选地，电机的转轴上固定有一支架，顶盖以及安装座通过螺栓固定在该支架上。
相比于现有技术，本发明利用外部空气对电机实施持续的风冷，确保电机始终处在低温环境下工作，提高了电机的稳定性以及可靠性，延长了电机的使用寿命，同时，可有效的防止雨水进入到外壳内部，确保电机正常工作。
针对现有技术的不足，本发明还需要提出一种旋翼飞行器的机臂与机身的连接结构，其不仅能够实现机臂与机身的快速拆卸和安装，同时还具有较强的防水性。
所述旋翼飞行器的机臂与机身的连接结构，包括机身以及机臂，其特征在于，机身周缘伸出有固定套管，固定套管外部设置有第一外螺纹，机臂的前端设置有一插装于固定套管内的插装头，插装头上设置有一突出于机臂外表面的凸起部，凸起部与机臂外表面之间形成一插装槽，且凸起部的前端形成一配合面；机臂上套接有锁紧螺母以及锁套，锁紧螺母螺接于第一外螺纹上，其后端具有抵接于凸起部后端面的拉紧端，固定套管的外端面与配合面之间夹持有一第一密封圈，锁套上具有一嵌置于插装槽的插入部，插入部的外表面设置有螺接于凸起部内表面的第二外螺纹，锁套上套接有一第二密封圈，该第二密封圈被夹持于锁套的外表面和锁紧螺母后端部内表面之间；机臂表面设有一凸缘，凸缘被夹持在凸起部的前端和插入部的前端面之间。
可选地，插装头以可拆卸的方式套接在机臂的前端。
可选地，固定套管内设置有母插头，插装头内设置有插装于母插头内的公插头。
可选地，插装头上设置有一径向向外延伸的延伸部，凸起部由延伸部的边缘向后延伸，配合面为延伸部的前端面。
可选地，插装头的表面设置有轴向延伸的凹槽，固定套管的内壁设置有嵌置于凹槽内的凸台。
相比于现有技术，本发明通过锁紧螺母和锁套将机臂和机身锁紧固定，实现机身与机臂的快速安装和拆卸，同时，利用螺纹锁紧的方式压紧密封圈，使机身和机臂连接处具有较强的防水密封性。
针对现有技术的不足，本发明还需要提出一种旋翼飞行器的脚架拆装结构，其能够实现脚架与旋翼飞行器机身的快速安装和拆卸。
所述旋翼飞行器的脚架拆装结构包括：设置在旋翼飞行器机身底壁且开口朝下的容置槽，容置槽的顶壁上开设有一插孔，容置槽的其中一个侧壁上开设有一卡槽；固定连接在脚架上且容纳于容置槽中的固定座，该固定座上固定有插装于卡槽内的嵌置件；活动的安装在固定座内的插销，该插销由固定座上表面穿出的部分形成一匹配的插入插孔内的插接端；弹性部件，其用于提供一个顶压插销以使插接端嵌置于插孔内的弹性应力；受压时带动插销向着远离插孔的方向运动的推杆。
可选地，插销上设置有一挡片，推杆的内侧套接在插销上并位于挡片上方。
可选地，脚架内固定有一连接座，弹性部件被限定在连接座和挡片之间，固定座螺接在连接座上。
可选地，固定座上设置有一限定推杆上下运动的限位槽。
可选地，固定座上设置有一固定槽，嵌置件为一固定在固定槽内并从固定槽伸出的卡片。
相比于现有技术，本发明可以实现脚架与机身的快速拆卸和安装，简化了旋翼飞行器的组装过程，同时能够方便旋翼飞行器零部件的更换以及维修。
本发明的附加方面和优点将在下面的描述中部分给出，部分将从下面的描述中变得明显，或通过本发明的实践了解到。
附图说明
本发明的上述和/或附加的方面和优点从结合下面附图对实施例的描述中将变得明显和容易理解，其中：
图1是根据本发明实施例的旋翼飞行器的整机图；
图2是根据本发明实施例的旋翼飞行器的电机散热结构的爆炸图；
图3是图2所示的电机散热结构的剖视图；
图4是图2所示的电机散热结构中的顶盖的结构示意图；
图5是根据本发明实施例的旋翼飞行器的机臂与机身的连接结构的示意图；
图6是5所示的机臂与机身的连接结构中的机臂的剖视图；
图7是图6中A区域的放大图；
图8是根据本发明实施例的旋翼飞行器的脚架拆装结构的结构示意图；
图9是图8中的脚架拆装结构的脚架的结构示意图；
图10是图8中的脚架拆装结构的脚架的结构示意图。
附图标记：
旋翼飞行器1000；
机身100；固定套管11；第一外螺纹111；凸台112；容置槽12；顶壁121；插孔122；卡槽123；
机臂200；机臂200的第一端201；机臂200的第二端202；锁紧螺母21；锁套22；插入部221；第二外螺纹222；插装头23；配合面231；凸起部232；内螺纹233；延伸部234；凹槽235；第一密封圈24；第二密封圈25；凸缘26；
螺旋桨300；
电机散热结构400；外壳410；进风口411；空气流道412；顶盖430；气流拨片431；导水面432；支架440；安装座450；
脚架500；固定座51；固定槽511；限位槽512；嵌置件52；插销53；挡片531；推杆54；弹性部件55；连接座56；
电机600。
具体实施方式
下面详细描述本发明的实施例，所述实施例的示例在附图中示出，其中自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。下面通过参考附图描述的实施例是示例性的，仅用于解释本发明，而不能理解为对本发明的限制。
在本发明的描述中，需要理解的是，术语“轴向”、“周向”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”、“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括一个或者更多个该特征。在本发明的描述中，“多个”的含义是两个或两个以上，除非另有明确具体的限定。
在本发明的描述中，需要说明的是，除非另有明确的规定和限定，术语“安装”、“相 连”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体地连接；可以是机械连接，也可以是电连接；可以是直接相连，也可以通过中间媒介间接相连，可以是两个元件内部的连通或两个元件的相互作用关系。对于本领域的普通技术人员而言，可以根据具体情况理解上述术语在本发明中的具体含义。
在本发明中，除非另有明确的规定和限定，第一特征在第二特征之“上”或之“下”可以包括第一和第二特征直接接触，也可以包括第一和第二特征不是直接接触而是通过它们之间的另外的特征接触。而且，第一特征在第二特征“之上”、“上方”和“上面”包括第一特征在第二特征正上方和斜上方，或仅仅表示第一特征水平高度高于第二特征。第一特征在第二特征“之下”、“下方”和“下面”包括第一特征在第二特征正下方和斜下方，或仅仅表示第一特征水平高度小于第二特征。
下面参考图1-图10描述根据本发明实施例的旋翼飞行器1000。如图1所示，根据本发明实施例的旋翼飞行器1000包括：机身100、机臂200和螺旋桨300。
机身100底部可以设有脚架500，脚架500对机身100起到支撑作用，并且在旋翼飞行器1000降落时起到减震作用。如图1所示，可选地，脚架500可以包括对称设置在机身100底部的多个，当然可选地，脚架500还是一个且设置在机身100底部的中部。
如图1所示，机臂200的第一端201(安装端、根部、前端)连接在机身100上，如图1所示，可选地，机臂200可以是多个，例如可以是四个、还可以是八个或者更多个。多个机臂200相对于机身100对称布置。每个机臂200的第二端202(自由端、末端、后端)上设有螺旋桨300，螺旋桨300水平设置在相应的机臂200上。
螺旋桨300由电机600驱动旋转，电机600可以是多个，电机600的数量可以与螺旋桨300的数量相同，即每个螺旋桨300均由一个电机600驱动旋转。可选地，电机600的安装位置与螺旋桨300的位置对应，即电机600也可以设置在相应的机臂200的第二端202处。
根据本发明实施例的旋翼飞行器1000还包括电机散热结构400、机臂200与机身100的连接结构和脚架500快速拆装结构。下面将分别对上述各个结构的具体实施方式进行详细说明。
下面参考图1-图4描述根据本发明实施例的旋翼飞行器1000的电机散热结构400。根据本发明实施例的旋翼飞行器1000的电机散热结构400包括：外壳410、顶盖430和安装座450。
如图1所示，外壳410设在机臂200的第二端202上，可选地，外壳410与机臂200的第二端202之间可以的固定连接，也可以是可拆卸的连接。外壳410为具有顶部开口和底部进风口411的空心结构，电机600的机体设在外壳410的内部，其中，可选地， 电机600的机体相对于外壳410可以是固定安装，也就是说，正常使用时，电机600相对于外壳410静止，由此可以使电机600对螺旋桨300的驱动更加稳定。优选地，电机600的机体相对于外壳410可拆卸地安装，由此可以方便电机600的更换与维修。可选地，电机600的转轴向上伸出外壳410，电机600的机体的周缘与外壳410的内壁之间形成有空气流道412。
可选地，进风口411可以是设置在外壳410侧壁的底部的小孔，小孔的数量可以是多个，如图2所示，小孔的形状可以是任意的，例如可以是圆形、长圆形、多边形或者非规则的形状均可，只要能够满足外部的空气从该进风口411进入到外壳410内的空气流道412即可。
可选地，外壳410的顶部开口可以是由外壳410的上端全部敞开构成，或者也可以是外壳410内的空气流道412的顶部敞开形成。
顶盖430同步连接于电机600的转轴上，顶盖430封盖于顶部开口的上方，顶盖430下表面与外壳410的顶端面之间形成有将空气流道412与外界连通的间隙，具体地，顶盖430的周缘的下表面与外壳410的顶端面之间形成有该间隙，由此可以使电机散热结构400更加合理，有利于形成气体循环。上述的进风口411、空气流道412以及间隙与外界环境形成一个连通的回路，顶盖430的下表面设置有多个气流拨片431。
安装座450固定在顶盖430上表面且用于与螺旋桨300连接，可选地，安装座450与螺旋桨300之间可以通过任何形式进行安装，例如螺纹连接、卡扣连接、焊接连接等，由此将螺旋桨300与安装座450固定，电机600驱动顶盖430旋转，进而顶盖430可以带动螺旋桨300转动。
换言之：外壳410固定于旋翼飞行器1000机臂200端部，外壳410为一具有顶部开口和底部进风口411的空心结构，进风口411可以是设置在外壳410侧壁的底部的小孔，小孔的数量可以是多个，电机600的机体安装在外壳410的内部，电机600机体的周缘与外壳410的内壁之间形成空气流道412，顶盖430同步在电机600的转轴上，并且该顶盖430位于外壳410的上方，即封盖于上述顶部开口的上方，顶盖430的周缘下表面与外壳410的顶端面之间形成一间隙，该间隙将空气流道412的上端部与外界连通，由此，上述的进风口411、空气流道412以及间隙与外界环境形成一个连通的回路，顶盖430的下表面设置有多个气流拨片431；安装座450固定于顶盖430的上表面，可以在安装座450上设置外螺纹，用于将螺旋桨300与安装座450固定，从而使电机600的转轴驱动螺旋桨300转动。
在电机600工作时，其转轴带动顶盖430旋转，顶盖430下表面设置的气流拨片431拨动外壳410内部的空气流动，在离心力的作用下，使外壳410顶部形成负压，气流在 空气流道412内部由下至上流动，外界环境中温度较低的空气由进风口411进入到空气流道412中，这些温度较低的空气与电机600的机体发生热交换，将热量带走并延顶盖430与外壳410顶端面之间的间隙流出，如此不断的形成气流循环，从而利用外界空气对电机600的机体进行降温，使电机600始终处在低温环境下工作，从而提高了电机600的稳定性、可靠性，延长了电机600的使用寿命。
为了增加外壳410内部气流的流量以及流速，上述的多个气流拨片431可以绕顶盖430的中心轴圆周阵列，气流拨片431的延伸方向可以与顶盖430的径向一致。优选地，每个气流拨片431可以呈三角形，且气流拨片431的顶端面和底端面之间的距离由内向外逐渐减小。
当然，也可以根据需要，将多个气流拨片431的分布设置为螺旋状，气流拨片431的延伸方向可以是与顶盖430的径向形成一个夹角。总之，无论气流拨片431如何在顶盖430上分布或无论设置成何种形状，只要在顶盖430转动时，气流拨片431能够拨动外壳410内部的气流向外流动，在外壳410顶部产生负压即可。
优选地，每个气流拨片431的内端(气流拨片431的邻近顶盖430的中心的端部)与顶盖430的中心之间均具有间隙。这样，每个气流拨片431的内端之间围绕限定出一个位于顶盖430中部的留空区域，当顶盖430随电机600的转轴旋转时，可以在该区域处形成负压。被吸入的空气气压低于外壳410内壁与电机600之间的空隙处的气压，因此电机内部的热气在气压差的作用下进入气流拨片431的内端所围成的负压区，再从空气流道412高速排出，起到电机散热的作用。
优选地，上述的顶盖430的上表面可以形成一个导水面432，该导水面432的高度由中间向边缘逐渐降低，顶盖430的直径大于外壳410顶部的直径，也就是说，顶盖430的边缘位于外壳410顶部边缘的外侧，这样一来，雨水顺延导水面432向下流动，不会从顶盖430与外壳410顶端面之间形成的间隙进入到外壳410内部，从而达到了防水的目的。
可选地，电机600的转轴上固定有一支架440，顶盖430以及安装座450可以通过螺栓固定在该支架440上，该结构可便于电机600的安装和更换。
相比于现有技术，本发明利用外部空气对电机600实施持续的风冷，确保电机600始终处在低温环境下工作，提高了电机600的稳定性以及可靠性，延长了电机600的使用寿命，同时，可有效的防止雨水进入到外壳410内部，确保电机600正常工作。
下面参考图1、图5-图7描述根据本发明实施例的旋翼飞行器1000的机臂200与机身100的连接结构。参见图1所示的示例，该示例中，旋翼飞行器1000包括四个机臂200，下面将以旋翼飞行器1000具有四个机臂200为例进行描述。根据本发明实施例的 旋翼飞行器1000的机臂200与机身100的连接结构包括：固定套管11、插装头23、锁套22和锁紧螺母21。
如图1、图5所示，固定套管11从机身100的周缘伸出，机身100的周缘伸出四个固定套管11，四个机臂200分别与四个固定套管11配合安装。如图5和图6所示，插装头23设在机臂200的第一端201(机臂200的邻近机身100的一端、前端)，插装头23用于插装于固定套管11内，具体地，插装头23在从机臂200的第一端201想向第二端的方向上套设在机臂200的第一端201处，也就是说如图5和图6所示，插装头23由前向后套装在机臂200的第一端201。
插装头23上设置有突出于机臂200外表面的凸起部232，凸起部232与机臂200外表面之间形成有插装槽，如图5和图6所示，凸起部232可以位于插装头23的第二端处，即凸起部232位于插装头23的后端处，凸起部232与机臂200的外表面之间具有间隙，该间隙形成为插装槽，由图5和图6可知，插装槽的开口朝向后方。锁套22套设在机臂200上，锁套22上具有嵌置于插装槽的插入部221，具体地，如图5和图6所示，插入部221位于锁套22的前端且向前插入到插装槽内。
可选地，插装头23以可拆卸的方式套接在机臂200的第一端201，例如插装头23可以与机臂200的第一端201通过螺纹连接的方式进行安装，或者插装头23还可以与机臂200的第一端201通过卡扣结构进行连接。
其中，插入部221与凸起部232可以螺纹连接，由此通过螺纹连接，可以使插入部221和凸起部232之间安装更加方便，进而使插装头23和锁套22安装方便，而且连接稳定。而且可以根据需要，调整插装头23和锁套22的紧合度。
锁紧螺母21套设在机臂200上，锁紧螺母21的第二端(后端)具有抵接于凸起部232第二端面(后端面)的拉紧端。锁紧螺母21与固定套管11螺纹连接，由此当插装头23在机臂200上安装稳定后，凸起部232的位置是固定的，当锁紧螺母21与固定套管11旋紧时，凸起部232对锁紧螺母21起到拉紧作用，保证锁紧螺母21的位置固定，由此保证固定套管11与锁紧螺母21之间的紧固稳定，而且固定套管11与锁紧螺母21之间通过螺纹连接，从而可以方便组装，而且可以根据需要，调整固定套管11与锁紧螺母21之间的紧合度。
具体地，如图5所示，固定套管11外表面设置有第一外螺纹111，锁紧螺母21螺接于第一外螺纹111上，由此可以达到锁紧螺母21与固定套管11之间螺纹连接的目的。插入部221的外表面设置有螺接于凸起部232内表面的第二外螺纹222，由此可以达到插入部221与凸起部232之间螺纹连接的目的。
优选地，如图5和图6所示，凸起部232的第一端(前端)形成有配合面231，固 定套管11的外端面(自由端面)与配合面231之间夹持有第一密封圈24，具体地，第一密封圈24套设在插装头23的外表面上，由此可以确保插装头23与固定套管11锁紧。可选地，插装头23上设置有一径向向外延伸的延伸部234，凸起部232由延伸部234的边缘向机臂200的第二端202方向延伸形成，配合面231为延伸部234的第一端面。
优选地，锁套22上套接有第二密封圈25，第二密封圈25夹持于锁套22的外表面和锁紧螺母21的第二端部(后端部)的内表面之间。第二密封圈25可为锁紧螺母21提供一定的预紧力，确保锁紧螺母21与固定套管11连接的牢固性。
换言之，如图1、图5-图7所示，机身100上设置有固定套管11，机臂200上设置有插装头23、锁紧螺母21和锁套22，固定套管11由机身100的周缘延伸出，外表面开设有第一外螺纹111，该固定套管11可以采用可拆卸的方式固定在机身100内部，例如，将机身100设置为上下扣合的上壳和下壳，将固定套管11预埋在下壳的半圆槽中，利用限位结构限定固定套管11沿其自身轴向的自由度，接着扣合上壳，将上壳和下壳固定，从而将固定套管11与机身100固定，当然，固定套管11与机身100的固定还可以采用其他的结构，这些结构通常为本领域技术人员所熟知，在这里不做详细介绍。
上述插装头23采用套接配合的方式设置在机臂200的前端，插装头23上具有一突出于机臂200外表面的凸起部232，该凸起部232与机臂200外表面之间形成一插装槽，可以是在插装头23上设置一径向向外延伸的延伸部234，凸起部232是由延伸部234向后延伸形成的，延伸部234的前端面形成一径向的配合面231，该配合面231与固定套管11的端面配合，在插装头23外部套接有一位于配合面231和固定套管11的端面之间的第一密封圈24；锁紧螺母21和锁套22均是套在机臂200上，锁紧螺母21螺纹连接于第一外螺纹111，其后端部抵接于凸起部232后端面的拉紧端，旋紧锁紧螺母21，其后端部的拉紧端可将插装头23向着靠近固定套管11的方向推动，使配合面231与固定套管11的端面充分夹紧第一密封圈24；锁套22上具有一嵌置在插装槽内的插入部221，该插入部221的外表面设置有第二外螺纹222，对应该第二外螺纹222，在凸起部232的内表面设置有内螺纹233，此外，在锁套22上还套接有一第二密封圈25，该第二密封圈25被夹持在锁套22的外表面和锁紧螺母21后端部内表面之间。机臂200的表面向外延伸有一凸缘26，凸缘26被夹持在延伸部234和插入部221的前端面之间。
在安装时，将锁套22、锁紧螺母21和插装头23依次套在机臂200的前端，然后将插装头23插入到固定套管11中，旋紧锁套22，利用第二外螺纹222和内螺纹233将插装头23和锁套22锁紧，也就是说，使凸缘26被夹紧在延伸部234和插入部221之间，然后旋紧锁紧螺母21，使配合面231和固定套管11的端面充分夹紧第一密封圈24，确保插装头23与固定套管11锁紧，当锁紧螺母21被旋紧后，其后端压紧第二密封圈25， 如此，完成机臂200与机身100的安装，由于上述结构中采用螺纹锁紧，可实现机臂200与机身100的快速拆卸和安装，同时，螺纹锁紧的方式可充分的压紧第一密封圈24和第二密封圈25，确保机臂200与机身100连接处的密封性，此外，在旋紧锁紧螺母21的过程中，第二密封圈25可为锁紧螺母21提供一定的预紧力，确保锁紧螺母21与固定套管11连接的牢固性。
可选地，固定套管11内和插装头23内分别设有用于电路导通的连接件。当机臂200与机身100组装完毕后，固定套管11内的连接件与插装头23内的连接件相互接触，便可以导通电路。其中，需要说明的是，该电路可以是电机600以及螺旋桨300的供电电路和/或控制电路等。由此可以方便电路的连接与导通。
其中固定套管11与插装头23内的连接件的结构可以是任意的，只要二者相互接触后保证电路的导通即可。例如固定套管11和插装头23内可以分别设有金属片，两个金属片相互接触即可满足电路导通的目的。优选地，固定套管11内设置有母插头，插装头23内设置有插装于母插头内的公插头，以此来确保电器元件的电路导通，而且可以快速、准确地对接。
插装头23的外表面设置有轴向延伸的凹槽235，固定套管11的内壁设置有嵌置于凹槽235内的凸台112。可选地，在上述的插装头23的表面设置有轴向延伸的凹槽235，固定套管11的内壁设置有嵌置于凹槽235内的凸台112，在插装时，凸台112嵌置与凹槽235中，由此不仅可以对机臂200与固定套管11的安装起到导引作用。而且可以在旋翼飞行器1000的每个机臂200上的插装头23上设置不同位置的凹槽235，在与机臂200对应的固定套管11上设置对应凹槽235位置的凸台112，可以确保机臂200能够正确的安装在对应的固定套管11上，从而快速识别不同机臂200的安装位置，以确保旋翼飞行器1000能够正常工作。
相比于现有技术，本发明通过锁紧螺母21和锁套22将机臂200和机身100锁紧固定，实现机身100与机臂200的快速安装和拆卸，同时，利用螺纹锁紧的方式压紧密封圈，使机身100和机臂200连接处具有较强的防水密封性。
下面参考图1、图8-图10描述根据本发明实施例的旋翼飞行器1000的脚架500快速拆装结构。参见图1所示的示例，该示例中，旋翼飞行器1000包括两个脚架500，两个脚架500相对于机身100的中心线对称布置在机身100的底部。每个脚架500与机身100具有两个连接端，有利地，每个脚架500的连接端均具有本发明实施例的脚架500快速拆装结构。如图1、图8-图10所示，根据本发明实施例的旋翼飞行器1000的脚架500快速拆装结构包括：设置在机身100底壁且开口朝下的容置槽12、固定座51、插销53、弹性部件55和推杆54。
如图8所示，容置槽12的顶壁121上设有插孔122，固定座51固定连接在脚架500上且容纳于容置槽12内，插销53可活动地安装在固定座51内，具体地，插销53在上下方向上可以移动，插销53从固定座51上表面穿出的部分形成有插接端，插接端匹配插入插孔122内。进一步地，容置槽12的侧壁上开设有卡槽123，固定座51上还设有嵌置件52，嵌置件52配合在卡槽123内，因此当前之间嵌置件52配合在卡槽123内，并且插销53端插入到插孔122内后，可以使固定座51固定在容置槽12内，从而起到将脚架500设在机身100上的目的。
进一步地，弹性部件55用于提供一个顶压插销53以使插接端嵌置于插孔122内的弹性应力，即弹性部件55被构造成常压缩的状态，由此可以顶压插销53。推杆54受压时带动插销53向着远离插孔122的方向运动，这样当需要拆卸脚架500的时候，可以对推杆54进行压制，从而使插销53脱离插孔122，此时再以嵌置件52为支点向下转动固定座51，从而将嵌置件52从卡槽123内脱出，进而将脚架500从机身100上快速拆卸下来。当然安装的过程中，先将嵌置件52插入到卡槽123内并以嵌置件52为支点向上推动固定座51，当固定座51配合在容置槽12后，由于弹性部件55的存在，插接端嵌置于插孔122内，由此完成安装。
可选地，固定座51上设有固定槽511，嵌置件52为定位在固定槽511内并从固定槽511伸出的卡片。固定座51上设有用于限定推杆54上下运动的限位槽512，由此可以对推杆54的运动起到限制和定位的作用。
如图10所述，可选地，插销53上设有挡片531，推杆54套设在插销53上并位于挡片531上方，由此可以起到通过推杆54向下推动插销53移动的作用。
换言之，根据本发明的一种旋翼飞行器1000脚架500快速拆装结构，其是在机身100的底壁开设开口朝下的容置槽12，在脚架500的顶端固定连接一固定座51，其中，容置槽12的顶壁121上开设有一插孔122，容置槽12的其中一个侧壁上开设有一卡槽123；固定座51的形状与容置槽12的形状一致，该固定座51容纳在容置槽12中，固定座51的一侧设置有一卡片，在固定座51容纳于容置槽12中后，卡片插装在卡槽123中；固定座51为中空结构，其内部设置有一可上下活动的插销53，该插销53的延伸方向与高度方向一致，插销53的上端部由固定座51的上表面穿出，该穿出的部分形成一个匹配的插入到插孔122内的插接端；插销53上套接有一弹簧，弹簧用于提供一个将插销53向上顶压以使插销53顶部的插接端插入到插孔122内的弹性应力，具体的是，弹簧可以是被卡装于固定座51的底部和插销53之间，也可以是被卡装于脚架500与插销53之间，总之，只要确保弹簧下部被支撑、上部顶压插销53即可，当然，为了确保弹簧的上端部能够将插销53向上顶压，可以在插销53上设置一顶压弹簧上端部的挡片 531，也就是说，弹簧被限定在挡片531与固定座51的底部之间，或弹簧被限定在挡片531与脚架500之间；在这里需要说明的是，弹簧提供推动插销53的弹性应力，其还可以是用其他弹性元件部件，例如弹性胶块等。插销53上还连接有一推杆54，在下压推杆54时，推杆54带动插销53向下运动，可以使插销53顶部的插接端从插孔122中脱离，具体的是，推杆54的内侧端套在插销53上并位于挡片531的上方，推杆54的外侧端穿过固定座51上开设的限位槽512伸出至固定座51外部，以便于操作，限位槽512则用于限定推杆54上下运动的形成，并且为推杆54的上下运动起到导向的作用。
本发明的上述快速拆装结构在实施拆卸时，向下拨动推杆54的外侧端，推杆54带动插销53向下运动，插销53顶部的插接端从插孔122中脱离，此时，将脚架500以卡片处为支点转动，使固定座51从容置槽12中脱离，从而快速的将脚架500从机身100上拆卸下来；在安装时，将卡片插入到卡槽123中，以卡片处为支点转动脚架500，当固定座51的上表面与容置槽12的顶壁121完全贴合后，插销53顶部的插接端恰好插入到插孔122中，在弹簧弹性应力的作用下，插销53不会从插孔122中脱离，从而将脚架500固定在机身100下方。
上述的卡片可以是与固定座51一体成型，也可以是分开制作，具体的是，在固定座51上开设有一固定槽511，卡片固定在固定槽511中并从固定槽511伸出，该卡片可以是铝片，也可以是其他能够嵌置在卡槽123内部的嵌置件52。
脚架500内固定有一连接座56，弹簧被限定在连接座56和挡片531之间，连接座56的外周缘开设有外螺纹，固定座51内部开设有与外螺纹匹配的内螺纹，从而将固定座51螺接在脚架500上。
相比于现有技术，本发明可以实现脚架500与机身100的快速拆卸和安装，简化了旋翼飞行器1000的组装过程，同时能够方便旋翼飞行器1000零部件的更换以及维修。
在本说明书的描述中，参考术语“一个实施例”、“一些实施例”、“示意性实施例”、“示例”、“具体示例”、或“一些示例”等的描述意指结合该实施例或示例描述的具体特征、结构、材料或者特点包含于本发明的至少一个实施例或示例中。在本说明书中，对上述术语的示意性表述不一定指的是相同的实施例或示例。而且，描述的具体特征、结构、材料或者特点可以在任何的一个或多个实施例或示例中以合适的方式结合。
尽管已经示出和描述了本发明的实施例，本领域的普通技术人员可以理解：在不脱离本发明的原理和宗旨的情况下可以对这些实施例进行多种变化、修改、替换和变型，本发明的范围由权利要求及其等同物限定。

Claims (29)

  1. 一种旋翼飞行器，其特征在于，包括：
    机身，所述机身底部设有脚架；
    机臂，所述机臂的第一端连接在所述机身上；
    螺旋桨，所述螺旋桨连接在所述机臂的第二端，所述螺旋桨由电机驱动旋转；
    电机散热结构，所述电机散热结构包括：
    外壳，所述外壳设在所述机臂的所述第二端上，所述外壳为具有顶部开口和底部进风口的空心结构，所述电机的机体设在所述外壳的内部，所述电机的机体的周缘与所述外壳的内壁之间形成有空气流道；
    顶盖，所述顶盖同步连接于所述电机的转轴上，所述顶盖封盖于所述顶部开口的上方，所述顶盖下表面与所述外壳的顶端面之间形成有将所述空气流道与外界连通的间隙，所述顶盖的下表面设置有多个气流拨片；以及
    安装座，所述安装座固定在所述顶盖上表面且用于与所述螺旋桨连接。
  2. 根据权利要求1所述的旋翼飞行器，其特征在于，所述多个气流拨片绕所述顶盖的中心轴线圆周阵列，所述气流拨片的延伸方向与所述顶盖的径向一致。
  3. 根据权利要求1所述的旋翼飞行器，其特征在于，每个所述气流拨片的内端与所述顶盖的中心之间均具有间隙。
  4. 根据权利要求1所述的旋翼飞行器，其特征在于，所述多个气流拨片分布为螺旋状。
  5. 根据权利要求1所述的旋翼飞行器，其特征在于，每个所述气流拨片呈三角形且所述气流拨片的顶端面和底端面之间的距离由内向外逐渐减小。
  6. 根据权利要求1所述的旋翼飞行器，其特征在于，所述顶盖的上表面设有导水面，所述导水面的高度由中间向边缘逐渐降低。
  7. 根据权利要求1所述的旋翼飞行器，其特征在于，所述顶盖的边缘位于所述外壳顶部边缘的外侧。
  8. 根据权利要求1所述的旋翼飞行器，其特征在于，所述电机的转轴上固定设有支架，所述顶盖以及所述安装座固定设在所述支架上。
  9. 根据权利要求1所述的旋翼飞行器，其特征在于，还包括机臂与机身的连接结构，所述机臂与机身的连接结构包括：
    固定套管，所述固定套管从所述机身的周缘伸出；
    插装头，所述插装头设在所述机臂的所述第一端且用于插装于所述固定套管内，所述插装头上设置有突出于所述机臂外表面的凸起部，所述凸起部与所述机臂外表面之间形成有插装槽；
    锁套，所述锁套套设在所述机臂上，所述锁套上具有嵌置于所述插装槽的插入部，所述插入部与所述凸起部螺纹连接；
    锁紧螺母，所述锁紧螺母套设在所述机臂上，所述锁紧螺母与所述固定套管螺纹连接，所述锁紧螺母的第二端具有抵接于所述凸起部第二端面的拉紧端。
  10. 根据权利要求9所述的旋翼飞行器，其特征在于，所述凸起部的第一端形成有配合面，固定套管的外端面与所述配合面之间夹持有第一密封圈。
  11. 根据权利要求9所述的旋翼飞行器，其特征在于，所述固定套管外表面设置有第一外螺纹，所述锁紧螺母螺接于第一外螺纹上。
  12. 根据权利要求9所述的旋翼飞行器，其特征在于，所述插入部的外表面设置有螺接于所述凸起部内表面的第二外螺纹。
  13. 根据权利要求9所述的旋翼飞行器，其特征在于，所述锁套上套接有第二密封圈，所述第二密封圈夹持于所述锁套的外表面和所述锁紧螺母的第二端部的内表面之间。
  14. 根据权利要求9所述的旋翼飞行器，其特征在于，所述机臂表面设有凸缘，所述凸缘被夹持在所述凸起部和和所述插入部之间。
  15. 根据权利要求9所述的旋翼飞行器，其特征在于，所述插装头以可拆卸的方式套接在所述机臂的所述第一端。
  16. 根据权利要求9所述的旋翼飞行器，其特征在于，所述固定套管内和所述插装头内分别设有用于电路导通的连接件。
  17. 根据权利要求16所述的旋翼飞行器，其特征在于，所述固定套管内设置有母插头，所述插装头内设置有插装于所述母插头内的公插头。
  18. 根据权利要求10所述的旋翼飞行器，其特征在于，所述插装头上设置有一径向向外延伸的延伸部，所述凸起部由所述延伸部的边缘向所述机臂的第二端方向延伸形成，所述配合面为所述延伸部的第一端面。
  19. 根据权利要求9所述的旋翼飞行器，其特征在于，所述插装头的外表面设置有轴向延伸的凹槽，所述固定套管的内壁设置有嵌置于所述凹槽内的凸台。
  20. 根据权利要求1所述的旋翼飞行器，其特征在于，还包括脚架拆装结构，所述脚架拆装结构包括：
    设置在所述机身底壁且开口朝下的容置槽，所述容置槽的顶壁上设有插孔，所述容置槽的侧壁上开设有卡槽；
    固定座，所述固定座固定连接在所述脚架上且容纳于所述容置槽内，所述固定座上设有嵌置件，所述嵌置件配合在所述卡槽内；
    插销，所述插销可活动地安装在所述固定座内，所述插销从所述固定座上表面穿出的部 分形成有插接端，所述插接端匹配插入所述插孔内；
    弹性部件，所述弹性部件用于提供一个顶压所述插销以使所述插接端嵌置于所述插孔内的弹性应力；
    推杆，所述推杆受压时带动所述插销向着远离所述插孔的方向运动。
  21. 根据权利要求20所述的旋翼飞行器，其特征在于，所述插销上设有挡片，所述推杆套设在所述插销上并位于所述挡片上方。
  22. 根据权利要求20所述的旋翼飞行器，其特征在于，所述脚架上设有连接座，所述弹性部件被限定在所述连接座和所述挡片之间，所述固定座与所述连接座螺纹连接。
  23. 根据权利要求20所述的旋翼飞行器，其特征在于，所述固定座上设有用于限定所述推杆上下运动的限位槽。
  24. 根据权利要求20所述的旋翼飞行器，其特征在于，所述固定座上设有固定槽，所述嵌置件为定位在所述固定槽内并从所述固定槽伸出的卡片。
  25. 一种旋翼飞行器的电机散热结构，其特征在于，包括：
    外壳，所述外壳设在所述旋翼飞行器的机臂的端部，所述外壳为具有顶部开口和底部进风口的空心结构，所述电机的机体固定安装在所述外壳的内部，所述电机的机体的周缘与所述外壳的内壁之间形成有空气流道；
    顶盖，所述顶盖同步连接于所述电机的转轴上，所述顶盖封盖于所述顶部开口的上方，所述顶盖的周缘下表面与所述外壳的顶端面之间形成有将所述空气流道与外界连通的间隙，所述顶盖的下表面设置有多个气流拨片；以及
    安装座，所述安装座固定在所述顶盖上表面且用于与所述旋翼飞行器的螺旋桨连接。
  26. 一种旋翼飞行器的机臂与机身的连接结构，其特征在于，包括：
    固定套管，所述固定套管从所述机身的周缘伸出；
    插装头，所述插装头设在所述机臂的第一端且用于插装于所述固定套管内，所述插装头上设置有突出于所述机臂外表面的凸起部，所述凸起部与所述机臂外表面之间形成有插装槽；
    锁套，所述锁套套设在所述机臂上，所述锁套上具有嵌置于所述插装槽的插入部，所述插入部与所述凸起部螺纹连接；
    锁紧螺母，所述锁紧螺母套设在所述机臂上，所述锁紧螺母与所述固定套管螺纹连接，所述锁紧螺母的第二端具有抵接于所述凸起部第二端面的拉紧端。
  27. 根据权利要求26所述的旋翼飞行器的机臂与机身的连接结构，其特征在于，所述凸起部的第一端形成有配合面，固定套管的外端面与所述配合面之间夹持有第一密封圈。
  28. 根据权利要求26所述的旋翼飞行器的机臂与机身的连接结构，其特征在于，所述 锁套上套接有第二密封圈，所述第二密封圈夹持于所述锁套的外表面和所述锁紧螺母的第二端部的内表面之间。
  29. 一种旋翼飞行器的脚架拆装结构，其特征在于，包括：
    设置在所述旋翼飞行器的机身底壁且开口朝下的容置槽，所述容置槽的顶壁上设有插孔，所述容置槽的侧壁上开设有卡槽；
    固定座，所述固定座固定连接在所述脚架上且容纳于所述容置槽内，所述固定座上设有嵌置件，所述嵌置件配合在所述卡槽内；
    插销，所述插销可活动地设在所述固定座内，所述插销从所述固定座上表面穿出的部分形成有插接端，所述插接端匹配插入所述插孔内；
    弹性部件，所述弹性部件用于提供一个顶压所述插销以使所述插接端嵌置于所述插孔内的弹性应力；
    推杆，所述推杆受压时带动所述插销向着远离所述插孔的方向运动。
PCT/CN2015/091753 2014-10-27 2015-10-12 旋翼飞行器及电机散热结构、机臂与机身的连接结构和脚架拆装结构 WO2016066009A1 (zh)

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ES15855700T ES2728409T3 (es) 2014-10-27 2015-10-12 Estructura de disipación de calor para motor de aeronave de alas rotatorias
PL15855700T PL3213995T3 (pl) 2014-10-27 2015-10-12 Struktura rozpraszająca ciepło dla silnika wiropłatu
AU2015341237A AU2015341237B2 (en) 2014-10-27 2015-10-12 Rotorcraft and heat dissipation structure for motor
EP15855700.9A EP3213995B1 (en) 2014-10-27 2015-10-12 Motor heat dissipation structure for a rotorcraft
EP17167044.1A EP3246251B1 (en) 2014-10-27 2015-10-12 Rotorcraft and connecting structure for arm and airframe of rotorcraft
EP17167048.2A EP3239044B1 (en) 2014-10-27 2015-10-12 Rotorcraft and assembly and disassembly structure for foot stand and airframe of rotorcraft
US15/484,395 US10501171B2 (en) 2014-10-27 2017-04-11 Rotorcraft and heat dissipation structure for motor
US15/484,194 US10611469B2 (en) 2014-10-27 2017-04-11 Rotorcraft and assembly and disassembly structure for foot stand and airframe of rotorcraft
US15/484,183 US11358709B2 (en) 2014-10-27 2017-04-11 Rotorcraft and connecting structure for arm and airframe of rotorcraft
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EP3239044A1 (en) 2017-11-01
US11358709B2 (en) 2022-06-14
US20170217599A1 (en) 2017-08-03
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