WO2018120163A1 - Aéronef à rotors multiples et procédé de déploiement et/ou de pliage de couvercle de protection d'hélice correspondant - Google Patents

Aéronef à rotors multiples et procédé de déploiement et/ou de pliage de couvercle de protection d'hélice correspondant Download PDF

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Publication number
WO2018120163A1
WO2018120163A1 PCT/CN2016/113831 CN2016113831W WO2018120163A1 WO 2018120163 A1 WO2018120163 A1 WO 2018120163A1 CN 2016113831 W CN2016113831 W CN 2016113831W WO 2018120163 A1 WO2018120163 A1 WO 2018120163A1
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WO
WIPO (PCT)
Prior art keywords
fuselage
propeller
rotor aircraft
pair
guards
Prior art date
Application number
PCT/CN2016/113831
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English (en)
Chinese (zh)
Inventor
刘利剑
Original Assignee
深圳市大疆创新科技有限公司
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
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN201680004165.3A priority Critical patent/CN107108026B/zh
Priority to PCT/CN2016/113831 priority patent/WO2018120163A1/fr
Publication of WO2018120163A1 publication Critical patent/WO2018120163A1/fr

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    • 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
    • B64U30/26—Ducted or shrouded rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C19/00—Aircraft control not otherwise provided for
    • 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
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B64U30/293—Foldable or collapsible rotors or rotor supports

Definitions

  • the present invention relates to a method of deploying and/or collapsing a multi-rotor aircraft and its propeller shield.
  • a multi-rotor aircraft generally includes a fuselage and a plurality of rotor structures extending circumferentially from the fuselage, each rotor structure being comprised of an arm and a power assembly supported via the arm.
  • the arms can be folded to the sides of the fuselage.
  • some aircraft with high safety requirements such as those used for self-timer, usually have a protective cover.
  • the protective cover is usually superimposed on the arm, and the protective cover will shorten the aircraft.
  • the battery life in addition, often causes the folding of the arm to fail, making the aircraft inconvenient to carry.
  • some protective covers are detachable protective covers.
  • a multi-rotor aircraft including a fuselage, and a plurality of propeller guards coupled to the fuselage, wherein at least one of the plurality of propeller guards is a collapsible boot
  • Each of the collapsible protective covers has a collapsed state and an unfolded state, and in the collapsed state, the collapsible protective cover is folded above or below the fuselage, in an unfolded state The collapsible protective cover projects from the peripheral side of the body.
  • each propeller guard includes a connecting portion through which the propeller guard is coupled to the fuselage.
  • each of the collapsible protective covers is rotatably coupled to the body such that the collapsible protective cover is switchable between an unfolded state and a collapsed state.
  • collapsible protective cover is at least a pair, and the two collapsible protective covers that form a pair are separated from opposite sides of the fuselage and are arranged at a wrong height.
  • each of the collapsible protective covers is rotatably connected to the fuselage about a rotating axis parallel to the heading or rolling axis of the aircraft to enable the collapsible protection
  • the cover can be changed between an unfolded state and a collapsed state.
  • the two collapsible protective covers that make up a pair overlap in a direction perpendicular to the heading axis of the aircraft.
  • the two collapsible protective covers constituting a pair are placed above and below the fuselage in the collapsed state.
  • the collapsible protective cover is at least two pairs, and the two collapsible protective covers on the same side of the two pairs are placed above and below the fuselage in the folded state. .
  • each of the collapsible protective covers includes a locking-unlocking structure, and the locking-unlocking structure is fixedly disposed on the connecting portion of the collapsible protective cover, and the a movable connection for fixing a position of the collapsible boot relative to the fuselage and for uncoupling the propeller guard from a fixed position to enable the connecting portion to drive the propeller protection
  • the cover rotates about the axis of rotation.
  • At least one of the plurality of propeller protection covers is a hood-integrated protective cover
  • each of the hood-integrated protective covers includes a cover body and a motor base, and the cover body is fixedly connected and supports the motor a base for loading at least one electric machine for driving propeller rotation of the aircraft.
  • the cover further includes a protection ring, and the protection ring is fixedly connected and supported by the motor base through a plurality of fixing members.
  • At least one of the plurality of fastening members is a hollow structure for passing control cables for controlling the motor.
  • a fixing member closest to the body of the plurality of fixing members is a hollow structure.
  • fastening members are equiangularly distributed; and/or the fastening member is a rib.
  • collapsible protective cover is simultaneously a hood-integrated protective cover.
  • hood-integrated protective cover is simultaneously a collapsible protective cover.
  • the plurality of propeller protection covers are a hood integrated protection cover and a collapsible protective cover.
  • the plurality of propeller guards are divided into two or more pairs, and the two collapsible protective covers of each pair are placed on opposite sides of the fuselage and are arranged in a wrong height.
  • the multi-rotor aircraft is a quadrotor including four propeller guards.
  • a pair of propeller guards are disposed near the fuselage head and disposed on two sides of the fuselage, and the other pair of propeller guards are disposed near the tail of the fuselage and disposed on both sides of the fuselage.
  • a pair of propeller guards close to the fuselage head are placed above and below the fuselage in the collapsed state and overlap in a direction perpendicular to the heading axis; a pair of propeller guards near the tail of the fuselage are In the collapsed state, it is also placed above and below the fuselage, and overlaps in the direction perpendicular to the heading axis.
  • a propeller guard deployment and/or collapsing method for a multi-rotor aircraft including a fuselage and a plurality of propeller guards, the method comprising:
  • the propeller protection cover when the propeller protection cover is located in one of the first position and the second position, the propeller protection cover is located on a circumference side of the fuselage, and the propeller protection cover is located in another one of the first position and the second position
  • the propeller guard is located above or below the fuselage.
  • the method further includes folding a pair of propeller guards above and below the fuselage, respectively.
  • the method further includes: folding a pair of propeller guards respectively located on opposite sides of the circumference side of the fuselage to above and below the fuselage and locking on the fuselage.
  • the method further includes: folding a pair of propeller guards respectively located on opposite sides of the circumference of the fuselage to above and below the fuselage, and continuing to rotate the pair of propeller guards to be perpendicular to the heading The directions of the shafts overlap and the pair of propeller guards are locked to the fuselage.
  • the method further includes: folding a pair of propeller guards close to the fuselage head and respectively located on opposite sides of the circumference of the fuselage, respectively, to the upper and lower sides of the fuselage and locked to the fuselage.
  • the method further includes: folding a pair of propeller guards close to the tail of the fuselage and respectively located on opposite sides of the circumference of the fuselage, respectively, to the upper and lower sides of the fuselage and locked to the fuselage.
  • the method further includes: folding a pair of propeller guards near the middle of the fuselage and respectively located on opposite sides of the circumference of the fuselage, respectively, to the upper and lower sides of the fuselage and locked to the fuselage.
  • the method further includes: folding two adjacent propeller guards on the same side of the circumference of the fuselage to the upper and lower sides of the fuselage, respectively.
  • the method further includes unlocking the propeller guard in the second position such that the propeller guard is rotatable about the rotating shaft; rotating the propeller guard to the rotating shaft Said first position; and
  • the propeller guard is locked to the fuselage in the first position such that the propeller guard cannot rotate about the axis of rotation.
  • the propeller protection cover deployment and/or folding method of the multi-rotor UAV and the multi-rotor aircraft provided by the embodiments of the present invention folds the propeller protection cover over the upper and lower sides of the fuselage, which is convenient for the user to carry and does not affect the machine.
  • the width of the body allows for a larger battery to be installed in the body, thus extending the life of the aircraft.
  • FIG. 1 is a top plan view showing a four-rotor aircraft in an unfolded state in an embodiment of the present invention.
  • FIG. 2 is a top plan view showing the quadrotor of FIG. 1 in a collapsed state.
  • Figure 3 is a front elevational view of the quadrotor of Figure 1 in an unfolded state.
  • Figure 4 is a front elevational view of the quadrotor of Figure 1 in a collapsed state.
  • Figure 5 is a side elevational view of the quadrotor of Figure 1 in an unfolded state.
  • Figure 6 is a side elevational view of the quadrotor of Figure 1 in a collapsed state.
  • Fig. 7 is a top plan view showing the three-rotor aircraft in an unfolded state according to an embodiment of the present invention.
  • Figure 8 is a top plan view showing the three-rotor aircraft of Figure 7 in a collapsed state.
  • Fig. 9 is a top plan view showing the six-rotor aircraft in an unfolded state according to an embodiment of the present invention.
  • Figure 10 is a top plan view showing the three-rotor aircraft of Figure 9 in a collapsed state.
  • FIG. 11 is a flow chart showing a method of unfolding and/or folding a propeller guard of a multi-rotor aircraft according to an embodiment of the present invention.
  • a component when referred to as being "fixed” or “mounted” to another component, it can be directly on the other component or can also be in the middle of the component. When a component is considered to be “set to” another component, it can be placed directly on another component or possibly with a centered component.
  • the term "and/or" used herein includes all and any combination of one or more of the associated listed items.
  • the quadrotor 10 includes a fuselage 110 and four rotor structures 120 coupled to the fuselage 110, each rotor structure 120 including a propeller shield 121.
  • each rotor structure 120 including a propeller shield 121.
  • words such as “above the fuselage”, “below the fuselage”, and “circumferential side of the fuselage”, etc. are used, wherein “above the fuselage” refers to the edge.
  • the direction of the aircraft's heading axis is located in the space above the fuselage.
  • the “lower side of the fuselage” refers to the space position under the fuselage along the heading axis of the aircraft.
  • the "peripheral side of the fuselage” means The six-sided space surrounding the fuselage removes any one or more of the remaining front, rear, left and right four-sided spaces after removing the upper and lower sides of the fuselage.
  • each of the propeller protection covers 121 is a machine (“motor base”) cover (“protective cover”) integrated protective cover, including a cover 122 and fixed to the cover 122 and covered by the cover 122 Supported motor base 123.
  • the motor base 123 is located at a central position of the cover 122 for mounting a power component (not shown) of the aircraft 10.
  • the power assembly includes a propeller device of the aircraft 10 and a motor (not shown) that drives the rotation of the propeller device.
  • the motor is mounted on the motor base 123
  • the propeller device is mounted on the motor shaft of the motor.
  • the motor base 123 carries a motor, and the motor of the motor extends axially downward to drive the propeller device located below the motor base 123 to rotate. In another embodiment, the motor of the motor extends axially to drive rotation of the propeller device above the motor base 123. In still another embodiment, the motor base 123 is loaded with two motors, wherein the motor of one motor extends axially downward, driving the propeller device under the motor base 123 to rotate, and the motor shaft of the other motor. Extending upwardly, the propeller device located above the motor base 123 is rotated, thus, the aircraft 10 is provided with a spare motor and a spare propeller device. In a fourth embodiment, the motor base 123 carries two motors that coaxially drive one propeller device to rotate.
  • the cover body 122 and the motor base 123 are fixedly connected by a fastening member 124 to support the motor base 123 and the power assembly loaded by the motor base 123.
  • the cover body 122 includes a guard ring 125 that is located on the outer side of the motor base 123.
  • the guard ring 125 is covered with a protective layer (not labeled).
  • the protective layer is made of an elastic material, for example, the protective layer may be made of a highly elastic material such as a polypropylene plastic foamed material or a foamed polystyrene polyethylene blend.
  • the guard ring 125 and the motor base 123 are fixedly connected by a fixing member 124. Further, the guard ring 125, the fastening member 124 and the motor base 123 can be formed by integral molding.
  • the number of the fastening members 124 may be plural, and the following four are exemplified.
  • At least one of the fastening members 124 is hollow, so that a control cable (not shown) starting from the inside of the body 110 reaches the motor mounted on the motor base 123 via the fastening member 124.
  • one of the fasteners 124 closest to the fuselage 110 is a hollow structure.
  • the four fastening members 124 are located in the same plane and are equiangularly distributed to reduce the influence on the rotor airflow and extend the life time of the aircraft 10.
  • the four fastening members 124 may be located in different planes, for example, a slight height difference between the end point of each fixing member 124 fixedly connected to the motor base 121 and the end point of the fixed connection protection ring 125.
  • the angle between each two adjacent fastening members 124 is the same or substantially the same, so that the fastening members 124 are equiangularly distributed.
  • equiangularly distributed fastening members 124 may be fixedly coupled to the motor base 123 and the guard ring 125, for example, two, three or more five, six, and the like.
  • the fastening member 124 is a rib in one embodiment.
  • Each propeller guard 120 further includes a connecting portion 126 located outside the guard ring 125 through which the propeller guard is coupled to the fuselage 110.
  • the propeller guard covers 120 are all collapsible protective covers, including the unfolded state shown in FIGS. 1, 3, and 5 and the collapsed state shown in FIGS. 2, 4, and 6.
  • the connecting portion 126 is a rotating connecting portion disposed at an upper edge or a lower edge of the body 110 and rotatable about a rotating axis parallel to the heading axis Y of the aircraft 10, thereby allowing the propeller guard 120 to be in an unfolded state and folded. Switch between states.
  • a rotating shaft (not shown) is disposed corresponding to the direction of the upper or lower edge of the fuselage 110 parallel to the heading axis Y of the aircraft 10, and the rotating shaft can be positive. It is located on the upper or lower edge of the fuselage 110, or at the upper edge or lower edge of the fuselage 110 slightly in the middle of the fuselage.
  • the connecting portion 126 of the propeller protection cover 120 includes a hole position (not shown) through which the hole is sleeved and rotates around the rotating shaft.
  • Each of the connecting portions 126 is further provided with a locking-unlocking structure (not shown), and the locking-unlocking structure can be fixedly disposed on the connecting portion of the collapsible protective cover, between the body and the body
  • the locking-unlocking structure locks the propeller guard in this position when the propeller guard 120 is in a particular position, and disengages the propeller guard 120 from a fixed position so that it can be parallel
  • the rotation axis of the heading axis Y of the aircraft 10 i.e., the rotation shaft
  • the locking-unlocking structure may be a protrusion (not shown) facing the body 110 on the connecting portion 126 and a fastener sleeved at the end of the protruding post.
  • the limiting slots (not shown) on the fuselage 110 cooperate, and the two ends of the limiting slot respectively correspond to two states of the propeller protection cover 120: an unfolded state and a collapsed state.
  • the fastener In the unfolded state, the fastener is tightened to fix the propeller protection cover 120 in the unfolded state; when the propeller protection cover 120 is switched to the collapsed state, the fastener is loosened, and the propeller protection cover 120 is rotated along the limit slot to receive In the assembled state, the fastener is tightened to fix the propeller cover 120 to the collapsed state.
  • the locking-unlocking structure may be a hole disposed on the connecting portion 126 and a pin matching the hole position, and the connecting portion 126 is located at an upper edge of the body 110 Or a position slightly lower than the center of the lower edge, the body 110 has a hole on each side of the rotating shaft, and the hole position can also be matched with the pin, wherein the hole position closer to the edge of the body corresponds to the hole In the unfolded state of the propeller guard 120, the propeller guard 120 is rotated to the hole on the connecting portion 126 to align the hole, and the pin is inserted into the aligned hole to fix the propeller cover 120 to the position.
  • the hole position far from the edge of the fuselage corresponds to the collapsed state of the propeller protection cover 120.
  • the propeller protection cover 120 When the propeller protection cover 120 is switched to the collapsed state, the overhead nail is loosened, and the propeller protection cover 120 is rotated to the hole position on the connection portion 126. Align the hole farther from the edge of the fuselage and fix it with a pin.
  • the propeller guard 120 is folded above or below the fuselage 110 in the collapsed state. Further, a portion of the propeller cover 120 is placed above the fuselage 110 and another portion is placed below the fuselage 110. Further, the propeller protection cover 120 is divided into two pairs, both of which are disposed on the left and right sides of the body 110, the first pair is adjacent to the head 111 of the body 110, and the second pair is adjacent to the tail 112 of the body 110. .
  • the first pair of propeller protection covers 120 are arranged at a wrong height, and the plane perpendicular to the heading axis Y of the aircraft 10 is a horizontal plane, and the two propeller protection covers 120 of the first pair are located on the horizontal planes of different heights, that is, the height is set, so that When the first pair of propeller guards 120 are in the collapsed state, they can overlap or partially overlap each other.
  • one of the propeller protection covers 120 of the first pair is connected to the lower right edge of the fuselage 110, and is rotated and folded under the fuselage 110; the other propeller protection cover 120 is connected to the left side of the fuselage 110.
  • the upper edge of the side is rotated and folded over the fuselage 110, and the two have overlap in the direction of the parallel heading axis Y after folding.
  • the second pair of propeller guards 120 are also disposed in a wrong height.
  • the two pairs of propeller guards 120 are located on different levels of the horizontal plane, one of which is connected to the upper edge of the right side of the fuselage 110, and the other is connected to the fuselage 110.
  • the lower edge of the left side is located above and below the fuselage 110, respectively, and overlaps in the direction of the parallel heading axis Y.
  • the left and right sides of the fuselage 110 are segmented with the roll axis of the fuselage 110 as a center line, and the two propeller guards 120 on the same side of the fuselage 110 are also set to a wrong height, that is, located at the machine
  • the two propeller guards 120 on the left side of the body 110 are in a staggered arrangement, such as in the embodiment shown in Figures 1-6, in the two propeller guards 120 on the left side of the fuselage 110, wherein the propellers near the head 111
  • the protective cover 120 is connected to the upper edge of the fuselage 110, and is located above the fuselage 110 after being folded.
  • the propeller protection cover 120 near the tail portion 112 is connected to the lower edge of the fuselage 110, and is located below the fuselage 110 after being folded;
  • the other two propeller guards 120 on the right side of the fuselage 110 are also arranged in a wrong height.
  • any propeller guard 120 and its opposite and adjacent two propeller guards 120 are arranged at a wrong height, so that not only can The lateral dimension of the aircraft 10 is minimized during folding, and the center of gravity of the aircraft can be balanced during flight of the aircraft 10.
  • propeller protection cover in the embodiment of the present invention The structure and principle of the propeller protection cover in the embodiment of the present invention are described above by taking a quadrotor as an example. However, it can be seen that the propeller protection cover in the embodiment of the present invention can also be applied to other multi-rotor aircraft, such as three-rotor, six-rotor, eight-rotor and the like.
  • a three-rotor aircraft 20 includes a fuselage 210 and three rotor structures 220 coupled to the fuselage 210.
  • One of the rotor structures 220 is located at the head 211 of the fuselage 210 and the other pair of rotor structures 220 are located at the tail 212 of the fuselage 210.
  • Each of the rotor structures 220 includes a propeller protection cover 221, which may be a hood-integrated protective cover, or may not all be a hood-integrated protective cover, for example, a propeller protective cover located at the head 211.
  • the 221 may not be a hood-integrated protective cover.
  • the propeller protection cover 221 may be either a collapsible protective cover or not a collapsible protective cover.
  • the propeller protection cover 221 located at the head portion 211 may not be a collapsible protective cover.
  • the three propeller protection covers 221 are both a hood-integrated protective cover and a collapsible protective cover.
  • Each of the propeller guards 221 is rotatably connected to the body 210 via a connecting portion 227, and the propeller guard 221 can be in the unfolded state shown in FIG. 7 and the folded state shown in FIG. 8 through the connecting portion 227. Switch between.
  • the connecting portion 227 also includes a locking-unlocking structure (not shown) that cooperates with a corresponding structure on the body 210 to fix the propeller guard 221 in an unfolded state or a collapsed state.
  • the connecting portion 227 of the propeller protection cover 221 located in the head portion 211 is disposed at the upper edge of the body 210, and therefore, the propeller protection cover 221 is folded over the body 211 in the folded state, of course.
  • the connecting portion 227 of the propeller protection cover 221 may be disposed at a lower edge of the body 210 to fit the propeller protection cover 221 below the body 210.
  • the connecting portion 227 of the pair of propeller guards 221 located at the tail portion 212 is disposed at an upper edge of the body 210, and is disposed at a lower edge of the body 210, so that the two propeller guards 221 are wrong on both sides of the body 210.
  • the high arrangement, when folded, is collapsed above the fuselage 210 and collapsed below the fuselage 210, which overlap in a direction perpendicular to the heading Ya of the aircraft 20.
  • a six-rotor aircraft 30 includes a fuselage 310 and six rotor structures 320 coupled to the fuselage 310 , wherein the first pair of rotor structures 320 are located in the fuselage 310 .
  • the head 311, the second pair of rotor structures 320 are located at the tail 312 of the fuselage 310, and the third pair of rotor structures 320 are located at the center 313 of the fuselage 310.
  • Each of the rotor structures 320 includes a propeller protection cover 321 which may be a hood-integrated protective cover or not all of the hood-integrated protective covers, for example, located at the head 311 and/or the tail portion.
  • the propeller guard 321 of 312 can be other types of protective covers.
  • the propeller protection cover 321 may be a collapsible protective cover, or may not all be a collapsible protective cover, or may be folded, but may be folded on the circumferential side of the body 310 according to actual conditions, for example,
  • the propeller guard 321 located at the head 311 and/or the tail 312 may be otherwise folded over the circumference of the fuselage 310.
  • the six propeller protection covers 321 are both a hood-integrated protective cover and a collapsible protective cover, and each propeller protective cover 321 is rotatably connected to the body 310 through a connecting portion 327 through
  • the connecting portion 327 can switch the propeller guard 321 between the unfolded state shown in FIG. 7 and the collapsed state shown in FIG.
  • the connecting portion 327 also includes a locking-unlocking structure (not shown) that cooperates with a corresponding structure on the body 310 to fix the propeller protection cover 321 in an unfolded state or a collapsed state.
  • the connecting portion 327 of the pair of propeller guards 321 located at the head portion 311 is disposed at the upper edge of the body 310, and one of the lower edges of the body 310, so that the two propeller guards 321 are The sides of the fuselage 310 are arranged at a wrong height.
  • one is folded over the fuselage 310, and one is folded under the fuselage 310, and the two overlap in a direction perpendicular to the heading axis Yb of the aircraft 30.
  • the connecting portion 327 of the pair of propeller guards 321 located at the tail portion 312 is disposed at an upper edge of the body 310, and is disposed at a lower edge of the body 310, so that the two propeller guards 321 are wrong on both sides of the body 310.
  • the high arrangement, when folded, is collapsed above the fuselage 310, one collapsed below the fuselage 310, and the two overlap in a direction perpendicular to the heading axis Yb of the aircraft 30.
  • the connecting portion 327 of the pair of propeller guards 321 located in the middle portion 313 is disposed on the upper edge of the body 310, and is disposed on the lower edge of the body 310, such that the two propeller guards 321 are in the body 310.
  • the sides are arranged in a wrong height. When folded, one is folded over the fuselage 310, and one is folded under the fuselage 310, and the two overlap in a direction perpendicular to the heading axis Yb of the aircraft 30.
  • the left and right sides of the body 310 are divided by the roll axis Xb of the body 310 as a center line, and the three propeller guards 321 located on the same side of the body 310 are pressed from the head 311 to the tail 312.
  • the order is respectively upper-lower-upper-lower-upper-lower, and the three propeller guards 321 on the left side are respectively arranged from the head 311 to the tail 312 in an upper-lower-upward height setting.
  • the three propeller guards 321 located on the right side are respectively arranged from the head 311 to the tail portion 312 in a lower-upper-downer height, so that any two adjacent propeller guards 321 on either side are also in error.
  • the high arrangement avoids the problem that the adjacent propeller guards 321 interfere with each other after being folded, and also makes the body 310 smaller and more compact.
  • each of the four rotorcraft 10, the three-rotor aircraft 20, and the six-rotor aircraft 30 is a hood-integrated protective cover and a collapsible protective cover
  • any propeller cover of the aircraft may be only a hood-integrated protective cover, and it is not required to be the collapsible protective cover as described in the above embodiment, or the propeller protective cover can be folded, but the folding manner can be Different from those described in the above embodiments, for example, folded on both sides of the fuselage or front and rear of the fuselage.
  • the hood-integrated protective cover described in the embodiment of the present invention may be used as part of the rotor according to actual needs, and the other part of the rotor is still disposed separately from the protective cover of the prior art.
  • the method is, for example, supporting the motor base by the arm, and the protective cover is further supported on the motor base; further, according to actual needs, the partial rotor can adopt the collapsible protective cover introduced by the embodiment of the present invention, and the other part of the rotor adopts other The method is closed, or the rotor and the fuselage are fixedly connected and cannot be folded.
  • a part of the rotor adopts a hood-integrated protective cover and a part or all of the rotor adopts a collapsible protective cover
  • it can also be subdivided into a hood-integrated protective cover and a collapsible protective cover applied to the same rotor.
  • a hood-integrated protective cover and a collapsible protective cover applied to the same rotor.
  • it is applied to the rotors A, B, and C of the three-rotor aircraft simultaneously;
  • the hood-integrated protective cover and the collapsible protective cover are applied to different rotors, for example, the hood-integrated protective cover is applied to the rotor A of the three-rotor aircraft.
  • the retractable protective cover is applied to the rotors B and C; the hood-integrated protective cover partially overlaps with the rotor of the collapsible protective cover application, for example, the hood-integrated protective cover is applied to the rotors A and B of the quadrotor aircraft.
  • the collapsible protective cover is applied to the rotors B, C, and D.
  • the hood-integrated protective cover is applied to the rotor A of the quadrotor
  • the collapsible protective cover is applied to the rotors A and B. C, D, etc.
  • the manner in which the collapsible protective cover is rotated about a rotating shaft parallel to the roll axis of the aircraft may also be employed.
  • a method for unfolding and/or folding a propeller protection cover of a multi-rotor aircraft includes:
  • the propeller protection cover when the propeller protection cover is located in one of the first position and the second position, the propeller protection cover is located on a circumference side of the fuselage, and the propeller protection cover is located in another one of the first position and the second position
  • the propeller guard is located above or below the fuselage.
  • the method may further include the step of folding a pair of propeller guards above and below the fuselage, respectively.
  • the method may further include the steps of folding a pair of propeller guards respectively located on opposite sides of the circumference of the fuselage to above and below the fuselage and locking to the fuselage.
  • the method may further include the steps of: respectively folding a pair of propeller guards respectively located on opposite sides of the circumference of the fuselage to the upper and lower sides of the fuselage, and continuing to rotate the pair of propeller guards so that It overlaps in a direction perpendicular to the heading axis and locks the pair of propeller guards on the fuselage.
  • the method may further include the steps of: folding a pair of propeller guards 121 close to the fuselage head and respectively located on opposite sides of the circumference of the fuselage, respectively, above and below the fuselage Locked on the fuselage.
  • the method may further include: folding a pair of propeller guards adjacent to the rear of the fuselage and respectively located on opposite sides of the circumference of the fuselage, respectively, to the upper and lower sides of the fuselage and locked to the machine Body.
  • the method further includes: folding a pair of propeller guards near the middle of the fuselage and respectively located on opposite sides of the circumference of the fuselage, respectively, to the upper and lower sides of the fuselage and locked to the fuselage on.
  • the method may further include: folding two adjacent propeller guards on the same side of the circumference of the fuselage to the upper and lower sides of the fuselage, respectively.
  • the method may further include the steps of: unlocking the propeller guard in the second position, the propeller guard being rotatable about the axis of rotation; Rotating the propeller guard to the first position; and
  • the propeller guard is locked to the fuselage in the first position such that the propeller guard cannot rotate about the axis of rotation of the multi-rotor aircraft.
  • the multi-rotor aircraft and the multi-rotor aircraft propeller protection cover deployment and/or folding method of the present invention support the power component of the aircraft by directly using the protective cover instead of the conventional arm to support the motor base. It not only solves the safety hazard of some aircrafts that are highly sensitive to safety, but also saves the arm and can be lighter and has a lighter airflow than the conventional UAV with both the organic arm and the protective cover. The superimposed effect is not generated, and thus the life time of the aircraft is not affected.
  • the propeller protection cover is arranged in a wrong height and is respectively folded over the upper and lower sides of the fuselage, which is convenient for the user to carry and does not affect the fuselage. The width allows for a larger battery to be installed in the body to extend the life of the aircraft.

Abstract

L'invention concerne des aéronefs à rotors multiples et un procédé de déploiement et/ou de pliage du couvercle de protection d'hélice correspondant. L'aéronef (10, 20, 30) comprend un fuselage (110, 210 310) et une pluralité de couvercles de protection d'hélice (121, 221, 321) raccordés au fuselage (110, 210, 310) ; au moins l'un de la pluralité de couvercles de protection d'hélice (121, 221, 321) étant un couvercle de protection pliable, et chaque couvercle de protection pliable présentant un état de pliage et un état de déploiement : dans l'état de pliage, le couvercle de protection pliable étant plié au-dessus ou au-dessous du fuselage (110, 210, 310), et dans l'état de déploiement, le couvercle de protection pliable s'étendant à partir de la périphérie du fuselage (110, 210, 310), ce qui le rend facile à porter et permet de faciliter l'allongement de la durée de vol de l'aéronef.
PCT/CN2016/113831 2016-12-30 2016-12-30 Aéronef à rotors multiples et procédé de déploiement et/ou de pliage de couvercle de protection d'hélice correspondant WO2018120163A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201680004165.3A CN107108026B (zh) 2016-12-30 2016-12-30 多旋翼飞行器及其螺旋桨保护罩展开及/或收合方法
PCT/CN2016/113831 WO2018120163A1 (fr) 2016-12-30 2016-12-30 Aéronef à rotors multiples et procédé de déploiement et/ou de pliage de couvercle de protection d'hélice correspondant

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PCT/CN2016/113831 WO2018120163A1 (fr) 2016-12-30 2016-12-30 Aéronef à rotors multiples et procédé de déploiement et/ou de pliage de couvercle de protection d'hélice correspondant

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CN109677600A (zh) * 2018-08-16 2019-04-26 深圳市格上格创新科技有限公司 一种可收缩无人机旋翼防护装置及无人机

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US20150377405A1 (en) * 2014-06-25 2015-12-31 Pearson Engineering Ltd Inspection systems
CN105235891A (zh) * 2015-01-04 2016-01-13 北京零零无限科技有限公司 一种可折叠的无人机
CN205221092U (zh) * 2015-11-06 2016-05-11 珠海华迈航空科技有限公司 四旋翼飞行器
WO2016112124A2 (fr) * 2015-01-08 2016-07-14 Vantage Robotics, Llc Véhicule aérien sans pilote à protection d'hélice et capacité de survie aux impacts élevée
CN105947202A (zh) * 2016-04-28 2016-09-21 乐视控股（北京）有限公司 一种可折叠的无人机及其使用方法
CN106081084A (zh) * 2016-07-11 2016-11-09 南京航空航天大学 一种便携式可折叠球形无人机
CN206358357U (zh) * 2016-12-30 2017-07-28 深圳市大疆创新科技有限公司 多旋翼飞行器

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US20150377405A1 (en) * 2014-06-25 2015-12-31 Pearson Engineering Ltd Inspection systems
CN105235891A (zh) * 2015-01-04 2016-01-13 北京零零无限科技有限公司 一种可折叠的无人机
WO2016112124A2 (fr) * 2015-01-08 2016-07-14 Vantage Robotics, Llc Véhicule aérien sans pilote à protection d'hélice et capacité de survie aux impacts élevée
CN205221092U (zh) * 2015-11-06 2016-05-11 珠海华迈航空科技有限公司 四旋翼飞行器
CN105947202A (zh) * 2016-04-28 2016-09-21 乐视控股（北京）有限公司 一种可折叠的无人机及其使用方法
CN106081084A (zh) * 2016-07-11 2016-11-09 南京航空航天大学 一种便携式可折叠球形无人机
CN206358357U (zh) * 2016-12-30 2017-07-28 深圳市大疆创新科技有限公司 多旋翼飞行器

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