WO2019119940A1 - 螺旋桨装配方法、组装夹具及螺旋桨 - Google Patents

螺旋桨装配方法、组装夹具及螺旋桨 Download PDF

Info

Publication number
WO2019119940A1
WO2019119940A1 PCT/CN2018/110002 CN2018110002W WO2019119940A1 WO 2019119940 A1 WO2019119940 A1 WO 2019119940A1 CN 2018110002 W CN2018110002 W CN 2018110002W WO 2019119940 A1 WO2019119940 A1 WO 2019119940A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
base
rivet
propeller
clamp
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2018/110002
Other languages
English (en)
French (fr)
Inventor
张正力
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Autel Robotics Co Ltd
Original Assignee
Autel Robotics Co Ltd
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 Autel Robotics Co Ltd filed Critical Autel Robotics Co Ltd
Publication of WO2019119940A1 publication Critical patent/WO2019119940A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/02—Riveting procedures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/10—Riveting machines
    • B21J15/14—Riveting machines specially adapted for riveting specific articles, e.g. brake lining machines
    • B21J15/142—Aerospace structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J15/00—Riveting
    • B21J15/38—Accessories for use in connection with riveting, e.g. pliers for upsetting; Hand tools for riveting
    • B21J15/42—Special clamping devices for workpieces to be riveted together, e.g. operating through the rivet holes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft

Definitions

  • the invention relates to the technical field of propeller production, in particular to a propeller assembly method, an assembly fixture and a propeller.
  • the propeller is an important part of the operation of the aircraft.
  • the aircraft drives the propeller to rotate at a high speed through a motor or a power mechanism to provide corresponding lift to the aircraft.
  • Existing propeller structures typically include a blade that is rotated to provide lift and a blade base that is coupled to the motor power take-off shaft.
  • a split propeller is available.
  • the blades of the split propeller are folded.
  • the blades are automatically deployed and maintained in a symmetrical state to continue to rotate under the high-speed operation of the motor by the action of centrifugal force.
  • the prior art has at least the following problems: current split-type propellers are typically riveted to secure the blade to the base of the blade. Due to the uncontrollable situation in the riveting process, it is difficult to ensure the balance of the torque after the riveting of the blade, and the requirements for the dynamic balance of the split propeller cannot be satisfied. Therefore, the assembly method of the conventional rivet riveting will result in a high defect rate of the product.
  • an embodiment of the present invention provides a propeller assembly method capable of ensuring dynamic balance of a propeller, an assembly jig used in the assembly method, and a propeller assembled by the assembly method.
  • the embodiment of the present invention provides the following technical solutions:
  • a propeller assembly method includes the steps of: using a rivet through a blade and a blade base to constrain the blade within a corresponding blade assembly position of the blade base, the blade being provided with at least Two; pre-applying pressure to the blade base to cause different blades to receive the same torque; force the riveting to the rivet to fix the blade in the blade assembly position.
  • the force riveting to the rivet specifically includes: applying pressure to all the rivets at the same time; adjusting the riveting height so that the torque received by the blade after riveting does not change.
  • pressure is applied to the rivet by a double-head machine.
  • the embodiment of the present invention further provides the following technical solutions:
  • a propeller assembly jig includes: a base, a surface of the base is provided with a fixing station for placing a blade base; a middle shaft of the clamp, the middle shaft of the clamp is disposed at the fixed station, along the Extending the axial direction of the base; the clamp middle shaft is for passing through the blade base to restrain the blade base to a fixed station; the pressing member, the pressing member and the a shaft of the clamp is connected away from one end of the base, reciprocally movable in an axial direction of the shaft of the clamp for applying pressure to the base of the blade; and a riveted joint, the corresponding setting of the riveted joint
  • the rivet arrangement of the blade base is used to apply force to the rivet.
  • the upper surface of the fixed station abuts the rivet head of the rivet passing through the blade base when the blade base is placed.
  • the extrusion is a nut; the nut is threadedly coupled to the shaft of the clamp.
  • the assembly fixture further includes a lock spring; the lock spring is a tension spring sleeved on the shaft of the clamp; the lock spring is respectively associated with the clamp base and the The extrusions abut.
  • the assembly fixture further includes an anti-scratch pad; the anti-scratch pad is disposed between the extrusion and the pad base.
  • the embodiment of the present invention further provides the following technical solutions:
  • a propeller comprising a plurality of symmetrically disposed blades and a blade base. Wherein the blade is mounted on the blade base using a propeller assembly method as described above.
  • the blade base includes an upper base and a lower base that are symmetrically disposed; the upper base and the lower base are coaxially disposed to cooperate to form a clamping portion for gripping the blade, A rivet hole for the rivet to pass through is coaxially disposed on the clamping portion.
  • the assembly method of the embodiment of the present invention applies pressure in two steps during the riveting process, first applying an adjustable pressure to the base of the blade to ensure that the blade is received in the base of the blade. The torque is equal. Then the rivet is pressed and riveted.
  • the assembly method has a high production yield and can be widely used in the production of split propellers.
  • FIG. 1 is a schematic structural view of an assembly jig according to Embodiment 1 of the present invention.
  • Figure 2 is a cross-sectional view of Figure 1;
  • FIG. 3 is a flow chart of a method of assembling a propeller according to Embodiment 2 of the present invention.
  • FIG. 1 is a schematic exploded view of a propeller assembly jig according to an embodiment of the present invention.
  • 2 is a cross-sectional view of an embodiment of the present invention.
  • the blades of the propeller have been fixed to the corresponding blade assembly positions of the blade base by rivets, and are clamped and fixed by the assembly jig to perform a corresponding riveting process to complete the assembly of the propeller.
  • the propeller assembly jig includes a base 11, a clamp center shaft 12, an extrusion member 13, and a rivet joint 14.
  • the paddle base 15 and the paddle 16 are clamped and fixed by the assembly jig, and the paddle 16 and the paddle base 15 are riveted and fixed by a rivet 17.
  • the surface of the base 11 is provided with a fixing station 111 for placing the blade base 15 .
  • the fixing station may be a recess provided on the surface of the base 11. It has a corresponding fit size depending on the specific structure of the blade base.
  • the susceptor 11 is formed by laminating two cylindrical plates 113 and 115 having different radii.
  • the fixed station 111 is disposed on the cylindrical shape 113 as a recess that cooperates with the blade base 15.
  • a plurality of snap structures 114 are also disposed on the fixed station 111 to engage with the bottom of the blade base 15 to fix the blade base 15 to the fixed station 111.
  • a clamp shaft 12 is disposed on the fixed station 111 and extends in the axial direction of the base.
  • the clamp center shaft 12 extends upwardly from the bottom of the base and has a radius width that is adapted to the through hole of the blade base 15.
  • the extrusion 13 is coupled to an end 121 of the clamp shaft 12 remote from the base.
  • the extrusion member 13 is a pressing mechanism for applying a certain pressure to the blade base.
  • connection between the extrusion 13 and the shaft 12 in the clamp is a movable connection. It is reciprocally movable in the axial direction of the shaft 12 in the jig. As the distance between the extrusion 13 and the base 11 changes, the amount of pressure applied by the extrusion 13 to the blade base 15 can be adjusted.
  • the extrusion member 13 can be realized simply by using a nut having a certain diameter.
  • the end 121 of the shaft 12 in the clamp may be provided with an external thread.
  • the nut 13 is screwed to the shaft 12 in the clamp.
  • the clamp center shaft 12 is used to pass through the through hole in the center of the blade base 15.
  • the snap structure between the base and the blade base stabilizes the blade base to a fixed station, ensuring that the blade base 15 does not displace during riveting assembly.
  • the operator can increase or decrease the pressure exerted on the blade base 15 by screwing the nut 13 to move the nut in the axial direction of the shaft 12 in the clamp.
  • an anti-scratch pad 18 can be added between the nut 13 and the paddle base 15.
  • the rivet joint 14 is provided corresponding to the rivet 17 of the blade base for rivet fastening to the rivet 17. As shown in FIG. 2, the rivet joint 14 is sleeved at the end of the rivet 17 during assembly.
  • a pressure mechanism e.g., machine tool, rivet gun, etc.
  • a lock spring 19 may be sleeved outside the shaft 12 of the clamp.
  • the lock spring 19 is a tension spring that is restrained between the clamp base 15 and the extrusion 13 (or the gasket) to provide a corresponding pulling force to prevent loosening.
  • the number of blades to be assembled is set to two, symmetrically disposed on both sides of the blade base.
  • the blade mounting position of the blade base is provided with a through hole through which the rivet passes, and the end of the blade tip of the blade is also provided with a corresponding rivet hole.
  • the rivets Prior to being clamped to the assembly jig, the rivets are first passed through the rivet holes and through holes of the blade to lock the blade to the blade mounting position of the blade base. Then, one side of the rivet head of the rivet is placed on the fixing station 111 of the base 11, so that the shaft 12 of the clamp passes through the through hole in the center of the blade base and is clamped by the extrusion member in the assembly. On the fixture.
  • the assembly fixture can also be adapted for assembly of propellers having other numbers of blades, and is not limited to the pair of blades shown in FIG.
  • the fixed station 111 is provided with a raised stepped surface 116 which is disposed at a position corresponding to the rivet of the blade base.
  • the rivet head of the rivet 17 abuts against the stepped surface 116. Therefore, the rivet head of the rivet 17 carries all of the pressure during the application of pressure by the extrusion or the application of the rivet joint.
  • the paddle base 15 does not directly abut the surface of the fixed station and does not carry the pressure exerted by the base 11.
  • FIG. 3 is a flowchart of a method for assembling a propeller according to an embodiment of the present invention.
  • the propeller assembly method provided by the embodiment of the present invention can be implemented by using an assembly jig as shown in FIG. Of course, it can also be done according to actual needs, using other suitable structure fixtures.
  • the assembly method includes the following steps:
  • the blades are constrained within a corresponding blade assembly position of the blade base, the blades being provided with at least two.
  • the paddles 16 may be provided in two, and the paddle base 15 is composed of an upper base 151 and a lower base 152.
  • the upper base 151 and the lower base 152 are coaxially disposed, and the symmetrical ends extend outwardly to form a clamping portion for gripping the blade 16.
  • Both the clamping portion and the paddle 16 are provided with through holes through which the rivets pass. Therefore, after the rivet passes through the through hole of the blade 16 and the nip portion, the paddle 16 can be restrained at the position of the nip portion.
  • step 120 is implemented by the nut 13 shown in FIG. After the nut 13 is screwed in the forward direction, the nut 13 can be pressed against the upper base 151 and the lower base 152, so that the blade clamped at the nip portion receives a corresponding moment.
  • the assembler can adjust the applied pressure by the number of turns of the nut 13, thereby ensuring that the blades 16 fixed to both sides of the blade base 15 are subjected to the same torque.
  • the corresponding force applying mechanism rivets the rivet 17 through the rivet joint 14 to fix the blade 16 at the corresponding position of the blade base 15. on.
  • the riveting process is controlled to ensure that the force of the blade 16 is not affected by the riveting.
  • a double-head machine can be used to provide the riveting pressure required for riveting.
  • any other suitable means can be used to complete the riveting process, such as manual manual operation.
  • the blade 16 after the riveting is completed can be rotated by the rivet 17 as a shaft.
  • it is folded, and in the state of use, the centrifugal force caused by the high-speed operation of the motor is opened, and the symmetry state is maintained.
  • the pressure for adjusting the dynamic balance and the riveting pressure applied at the time of riveting are separately controlled during the assembly process. Therefore, in the production assembly, the pressure can be adjusted before the riveting is completed, and there is no problem of imbalance between the different blades, thereby improving the qualification rate of the propeller assembly.
  • the step 130 specifically includes:
  • the force applied in the first step is a pre-pressure
  • the pre-pressure can be adjusted to ensure that the blade receives the same magnitude of torque.
  • the riveting force applied in the second step is used to fix the paddle and the blade base, maintaining the pre-pressure applied in the first step. In this way, the dynamic balance of the blade can be improved, and the production yield of the product can be improved.
  • the embodiment of the present invention further provides a propeller obtained by assembling the above propeller assembly method. Since the propeller adopts the step-by-step riveting method in the assembly process, the blades receive the same torque, so that when the blades rotate, the frictional force is the same, which makes the aircraft balance when starting, and can achieve stable starting and flying.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automatic Assembly (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种螺旋桨的装配方法，包括：使用铆钉（17）穿过桨叶（16）以及桨叶基座（15），将桨叶（16）限制在所述桨叶基座（15）对应的桨叶（16）装配位内，所述桨叶（16）至少设置有两个。预先向桨叶基座（15）施加压力，令不同的桨叶（16）受到相同的力矩；向铆钉（17）施力铆接，以使桨叶（16）固定在桨叶（16）装配位。还涉及装配螺旋桨的组装夹具及采用该方法装配的螺旋桨。该装配方法分两步进行施压，便于在组装过程中控制桨叶受到的力矩，确保桨叶的动平衡，生产合格率较高。

Description

螺旋桨装配方法、组装夹具及螺旋桨
【相关申请的交叉引用】
本申请要求申请号为201711405479.7，申请日为2017年12月22日申请的中国专利申请的优先权，其全部内容通过引用结合于本文。
【技术领域】
本发明涉及螺旋桨生产技术领域，尤其涉及一种螺旋桨装配方法、组装夹具及螺旋桨。
【背景技术】
螺旋桨是飞行器运行的重要部件。飞行器通过马达或者动力机构带动螺旋桨高速旋转从而为飞行器提供相应的升力。现有的螺旋桨结构一般包括了通过旋转以提供升力的桨叶以及与马达动力输出轴连接的桨叶基座。
基于节省收纳空间，便于飞行器放置等要求，现有一种甩开式螺旋桨。在非使用状态下，甩开式螺旋桨的桨叶收折。而在飞行器运行时，桨叶在马达的高速运转下，通过离心力的作用实现自动展开并保持对称状态继续旋转。
在这样的螺旋桨中，桨叶与桨叶基座之间采用的是活动式连接。因此在螺旋桨的桨叶展开过程以及展开后的旋转过程中，对于桨叶的动平衡要求很高。
在实现本发明的过程中，发明人发现现有技术至少存在以下问题：目前的甩开式螺旋桨通常采用铆钉铆接的方式，将桨叶固定在桨叶基座上。由于铆接过程中的容易出现不可控的情况，难以很好的保证桨叶铆接后的力矩平衡，不能满足甩开式螺旋桨对于动平衡的要求。因此，传统铆钉铆接的组装方式，会导致产品的不良率较高。
【发明内容】
为了解决上述技术问题，本发明实施例提供一种能够保证螺旋桨动平衡 的螺旋桨装配方法、该装配方法使用的组装夹具及由该装配方法组装的螺旋桨。
为解决上述技术问题，本发明实施例提供以下技术方案：
一种螺旋桨装配方法，包括如下步骤：使用铆钉穿过桨叶以及桨叶基座，将所述桨叶限制在所述桨叶基座对应的桨叶装配位内，所述桨叶至少设置有两个；预先向所述桨叶基座的施加压力，令不同的桨叶受到相同的力矩；向所述铆钉施力铆接，以使所述桨叶固定在所述桨叶装配位。
在一些实施例中，所述向所述铆钉施力铆接，具体包括：对所有铆钉同时施加压力；调整铆接高度，令所述桨叶在铆接后，受到的力矩不发生变化。
在一些实施例中，通过双头机床向所述铆钉施加压力。
为解决上述技术问题，本发明实施例还提供以下技术方案：
一种螺旋桨组装夹具，包括：基座，所述基座的表面设置有用于放置桨叶基座的固定工位；夹具中轴，所述夹具中轴设置在所述固定工位上，沿所述基座的轴向方向延伸；所述夹具中轴用于穿过所述桨叶基座，将所述桨叶基座限制在固定工位上；挤压件，所述挤压件与所述夹具中轴远离所述基座的一端连接，可沿所述夹具中轴的轴向方向往复移动，用于向所述桨叶基座施加压力；以及铆接头，所述铆接头设置对应所述桨叶基座的铆钉设置，用于向铆钉施力铆接。
在一些实施例中，所述固定工位的上表面在放置有所述桨叶基座时，与穿过所述桨叶基座的铆钉的铆钉头部相抵接。
在一些实施例中，所述挤压件为螺母；所述螺母与所述夹具中轴通过螺纹连接。
在一些实施例中，所述组装夹具还包括防松弹簧；所述防松弹簧为拉伸弹簧，套设在所述夹具中轴上；所述防松弹簧分别与所述夹具基座以及所述挤压件相抵接。
在一些实施例中，所述组装夹具还包括防划垫片；所述防划垫片设置在所述挤压件与桨叶基座之间。
为解决上述技术问题，本发明实施例还提供以下技术方案：
一种螺旋桨，包括若干个对称设置的桨叶以及桨叶基座。其中，所述桨叶应用如上所述的螺旋桨装配方法装配于所述桨叶基座上。
在一些实施例中，所述桨叶基座包括对称设置的上基座和下基座；所述上基座和下基座同轴设置，配合形成用于夹持桨叶的夹持部，所述夹持部上同轴设置有用于供铆钉穿过的铆钉孔。
与现有技术相比较，本发明实施例的装配方法在铆接过程中，分两步进行施压，首先对桨叶基座施加一个可调节的压力来保证桨叶在桨叶基座中受到的力矩相等。然后再对铆钉施压进行铆接。
通过这样的方式，可以便于在组装过程中控制桨叶受到的力矩，确保桨叶的动平衡，在甩开和运行过程中受到相同的摩擦力，符合甩开式螺旋桨的使用要求。该装配方法的生产合格率高，可以广泛应用于甩开式螺旋桨的生产中。
【附图说明】
一个或多个实施例通过与之对应的附图中的图片进行示例性说明，这些示例性说明并不构成对实施例的限定，附图中具有相同参考数字标号的元件表示为类似的元件，除非有特别申明，附图中的图不构成比例限制。
图1为本发明实施例1的组装夹具的结构示意图；
图2为图1所示的剖视图；
图3为本发明实施例2的螺旋桨装配方法的方法流程图。
【具体实施方式】
为了便于理解本发明，下面结合附图和具体实施例，对本发明进行更详细的说明。需要说明的是，当元件被表述“固定于”另一个元件，它可以直接在另一个元件上、或者其间可以存在一个或多个居中的元件。当一个元件被表述“连接”另一个元件，它可以是直接连接到另一个元件、或者其间可以存在一个或多个居中的元件。本说明书所使用的术语“上”、“下”、“内”、“外”、“底部”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”“第三”等仅用于描述目的，而不能理解为指示或暗示相对重要性。
除非另有定义，本说明书所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。本说明书中在本发明的说明书中所使用的术语只是为了描述具体的实施例的目的，不是用于限制本发明。本说明书所使用的术语“和/或”包括一个或多个相关的所列项目的任意的和所有的组合。
此外，下面所描述的本发明不同实施例中所涉及的技术特征只要彼此之间未构成冲突就可以相互结合。
实施例1
图1为本发明实施例提供的螺旋桨组装夹具的分解结构示意图。图2为本发明实施例提供的剖视图。在本实施例中，螺旋桨的桨叶已经通过铆钉固定在桨叶基座相应的桨叶装配位上，被组装夹具夹持固定，以进行相应的铆接工序，完成螺旋桨的装配。
如图1所示，该螺旋桨组装夹具包括：基座11、夹具中轴12、挤压件13以及铆接头14。桨叶基座15和桨叶16由该组装夹具夹持固定，桨叶16和桨叶基座15之间通过铆钉17铆接固定。
其中，基座11的表面设置有用于放置桨叶基座15的固定工位111。该固定工位可以是设置在基座11表面的凹陷。其根据桨叶基座的具体结构，具有相应的适配尺寸。
在本实施例中，该基座11由两个半径不同的圆柱形113和115层叠形成。固定工位111设置在圆柱形113上，为与桨叶基座15相配合的凹陷。固定工位111上还设置有若干个卡扣结构114，与桨叶基座15的底部相互扣合，将桨叶基座15固定在固定工位111上。
夹具中轴12设置在所述固定工位111上，沿所述基座的轴向方向延伸。该夹具中轴12从基座的底部向上延伸，具有与桨叶基座15的通孔相适配的半径宽度。
挤压件13与所述夹具中轴12远离所述基座的一端121连接。挤压件13是一个施压机构，用于向所述桨叶基座施加一定的压力。
在本实施例中，挤压件13与夹具中轴12之间的连接为活动式的连接。其可沿所述夹具中轴12的轴向方向往复移动。随着挤压件13与基座11之间的距离变化，可以调整挤压件13对于桨叶基座15施加的压力大小。
具体的，如图2所示，该挤压件13可以简单的采用具有一定直径宽度的螺母来实现。在夹具中轴12的末端121可以设置有外螺纹。螺母13与夹具中轴12之间通过螺纹连接。
在实际装配过程中，如图2所示，夹具中轴12用于穿过所述桨叶基座15中心的通孔。基座和桨叶基座之间的卡扣结构将所述桨叶基座稳定的限制在固定工位上，确保桨叶基座15在铆接装配时不会发生位移等情况。操作人员可以通过旋拧螺母13，使螺母沿夹具中轴12的轴向方向运动，从而增加或者减少施加在桨叶基座15上的压力。
螺母13在旋拧过程中，若直接与桨叶基座的表面相接，很可能会因为边角和施加的压力造成桨叶基座表面的划伤，不符合产品的制作要求。在另一些实施例中，如图1所示，可以在螺母13和桨叶基座15之间增设一防划伤垫片18。
如图2所示，通过额外设置的防划伤垫片18，可以避免螺母13与桨叶基座15的表面直接接触，不会因旋拧螺母13而划伤桨叶基座15的表面。
铆接头14与所述桨叶基座的铆钉17对应设置，用于向铆钉17施力铆接。如图2所示，在装配过程中，铆接头14套设在铆钉17的末端。压力机构(例如机床，铆枪等)可以通过铆接头14向铆钉17施加压力，完成桨叶16和桨叶基座15之间的铆接。
可选地，如图2所示，夹具中轴12外还可以套设有防松弹簧19。该防松弹簧19为拉伸弹簧，限制在夹具基座15和挤压件13(或垫片)之间，提供相应的拉力以防止出现松脱的情况。
在本实施例中，需要装配的桨叶数量设置为两个，对称设置于桨叶基座的两侧。桨叶基座的桨叶装配位上设置有供铆钉穿过的通孔，桨叶的叶柄末端也设置有相应的铆钉孔。在夹装到组装夹具前，首先使用铆钉穿过桨叶的铆钉孔和通孔，将桨叶卡止在桨叶基座的桨叶装配位上。然后，将铆钉的铆钉头部的一面放置在基座11的固定工位111上，令夹具中轴12穿过所述桨叶基座中心的通孔并通过挤压件将其夹持在组装夹具上。
在另一些实施例中，该组装夹具还可以适用于具有其他桨叶数量的螺旋桨的装配，而不限于图1所示的一对桨叶。
如图1所示，在本实施例中，固定工位111上设置有凸起的台阶面116， 其设置在与桨叶基座的铆钉相对应的位置。如图2所示，桨叶基座15在扣合固定以后，铆钉17的铆钉头部会与该台阶面116相抵接。因此，在挤压件施加压力或者铆接头施力的过程中，铆钉17的铆钉头部会承载全部的压力。而桨叶基座15则不直接与固定工位的表面相抵，不承载由基座11施加的压力。
实施例2
图3为本发明实施例提供的螺旋桨装配方法的方法流程图。本发明实施例提供的螺旋桨装配方法可以应用如图1所示的组装夹具来实现。当然，也可以根据实际需要，使用其他合适结构的工装夹具来完成。
如图3所示，所述装配方法包括如下步骤：
110、使用铆钉穿过桨叶以及桨叶基座，将所述桨叶限制在所述桨叶基座对应的桨叶装配位内，所述桨叶至少设置有两个。
在本实施例中，如图2所示，桨叶16可以设置为两个，桨叶基座15由上基座151和下基座152组成。上基座151和下基座152同轴设置，对称的两端向外延伸配合形成用于夹持桨叶16的夹持部。夹持部和桨叶16上均设置有供铆钉穿过的通孔。因此，在铆钉穿过桨叶16和夹持部的通孔以后，便可以将桨叶16限制在该夹持部的位置上。
120、预先向所述桨叶基座的施加压力，令不同的桨叶受到相同的力矩。
在本实施例中，步骤120由图1所示的螺母13实现。沿正向旋拧螺母13以后，可以令螺母13对上基座151和下基座152进行挤压，从而令夹持在夹持部的桨叶受到相应的力矩。装配人员可以通过螺母13的旋拧圈数来调整施加的压力大小，从而确保固定在桨叶基座15两侧的桨叶16均受到相同的力矩。
130、向所述铆钉施力铆接，以使所述桨叶固定在所述桨叶装配位。
在旋拧螺母13，向桨叶基座15施加合适的预压力以后，相应的施力机构会通过铆接头14对铆钉17施力铆接，将桨叶16固定在桨叶基座15相应的位置上。当然，在铆接过程中，对铆接过程进行控制，确保桨叶16的受力不受到铆接的影响。
具体的，可以使用双头机床提供铆接时需要的铆接压力。当然还可以使用其他任何合适的方式来完成铆接工序，例如人工手动操作等。
铆接完成后的桨叶16可以铆钉17为轴旋转。在非使用状态下收折，并 在使用状态下，随马达高速运转带来的离心力甩开，保持对称状态旋转。
在本实施例中，在装配过程中，调整动平衡的压力与铆接时施加的铆接压力是分开的控制。因此，在生产装配时，可以调整压力后再完成铆接，不存在不同桨叶之间力不平衡的问题，从而提高了螺旋桨装配的合格率。
在另一些实施例中，所述步骤130具体包括：
首先，在保持步骤120的压力的前提下，同时对全部铆钉17施加压力。然后，在铆接过程中，通过调整铆接高度的方式，令桨叶16在铆接后，受到的力矩不发生变化。
上述铆接过程中，不会把力传导到桨叶16与桨叶基座15中，铆接过程中的施力只是用于保持步骤120提供的预压力，并非对桨叶16的受力进行控制。该铆接力不会影响最终螺旋桨成品的动平衡。
综上所述，本发明实施例提供的螺旋桨装配方法中，第一步施加的力为预压力，可以调整预压力从而确保桨叶受同样大小的力矩。第二步施加的铆接力用于固定桨叶和桨叶基座，保持第一步中施加的预压力。通过这样的方式，可以令桨叶的动平衡良好，提高产品的生产合格率。
本发明实施例还进一步提供了一种应用上述螺旋桨装配方法装配获得的螺旋桨。由于螺旋桨在装配过程中采用的是分步铆接的方式，桨叶受到的力矩相同，从而使桨叶旋转时，受到的摩擦力一致，令飞行器启动时动力平衡，能够实现稳定的启动和飞行。
最后应说明的是：以上实施例仅用以说明本发明的技术方案，而非对其限制；在本发明的思路下，以上实施例或者不同实施例中的技术特征之间也可以进行组合，步骤可以以任意顺序实现，并存在如上所述的本发明的不同方面的许多其它变化，为了简明，它们没有在细节中提供；尽管参照前述实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的范围。

Claims (10)

  1. 一种螺旋桨装配方法，其特征在于，包括：
    使用铆钉穿过桨叶以及桨叶基座，将所述桨叶限制在所述桨叶基座对应的桨叶装配位内，所述桨叶至少设置有两个；
    预先向所述桨叶基座的施加压力，令不同的桨叶受到相同的力矩；
    向所述铆钉施力铆接，以使所述桨叶固定在所述桨叶装配位。
  2. 根据权利要求1所述的方法，其特征在于，所述向所述铆钉施力铆接，具体包括：
    对所有铆钉同时施加压力；
    调整铆接高度，令所述桨叶在铆接后，受到的力矩不发生变化。
  3. 根据权利要求1所述的方法，其特征在于，通过双头机床向所述铆钉施加压力。
  4. 一种螺旋桨组装夹具，其特征在于，包括：
    基座，所述基座的表面设置有用于放置桨叶基座的固定工位；
    夹具中轴，所述夹具中轴设置在所述固定工位上，沿所述基座的轴向方向延伸；所述夹具中轴用于穿过所述桨叶基座，将所述桨叶基座限制在固定工位上；
    挤压件，所述挤压件与所述夹具中轴远离所述基座的一端连接，用于向所述桨叶基座施加压力；
    铆接头，所述铆接头设置对应所述桨叶基座的铆钉设置，用于向铆钉施力铆接。
  5. 根据权利要求4所述的螺旋桨组装夹具，其特征在于，所述固定工位设置有凸起的台阶面，与穿过所述桨叶基座的铆钉的铆钉头部相抵接。
  6. 根据权利要求4所述的螺旋桨组装夹具，其特征在于，所述挤压件为螺母；所述螺母与所述夹具中轴通过螺纹连接。
  7. 根据权利要求4所述的螺旋桨组装夹具，其特征在于，还包括：防松弹簧；
    所述防松弹簧为拉伸弹簧，套设在所述夹具中轴上；所述防松弹簧分别与所述夹具基座以及所述挤压件相抵接。
  8. 根据权利要求4所述的螺旋桨组装夹具，其特征在于，还包括防划垫片；所述防划垫片设置在所述挤压件与桨叶基座之间。
  9. 一种螺旋桨，包括若干个对称设置的桨叶以及桨叶基座，其特征在于，
    所述桨叶应用如权利要求1-3任一所述的螺旋桨装配方法装配于所述桨叶基座上。
  10. 根据权利要求9所述的螺旋桨，其特征在于，所述桨叶基座包括对称设置的上基座和下基座；
    所述上基座和下基座同轴设置，配合形成用于夹持桨叶的夹持部，所述夹持部上设置有用于供铆钉穿过的铆钉孔；所述桨叶的末端设置有用于与所述铆钉孔对应的通孔。
PCT/CN2018/110002 2017-12-22 2018-10-12 螺旋桨装配方法、组装夹具及螺旋桨 Ceased WO2019119940A1 (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201711405479.7A CN108127066B (zh) 2017-12-22 2017-12-22 螺旋桨装配方法、组装夹具及螺旋桨
CN201711405479.7 2017-12-22

Publications (1)

Publication Number Publication Date
WO2019119940A1 true WO2019119940A1 (zh) 2019-06-27

Family

ID=62391614

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2018/110002 Ceased WO2019119940A1 (zh) 2017-12-22 2018-10-12 螺旋桨装配方法、组装夹具及螺旋桨

Country Status (2)

Country Link
CN (1) CN108127066B (zh)
WO (1) WO2019119940A1 (zh)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108127066B (zh) * 2017-12-22 2019-06-25 深圳市道通智能航空技术有限公司 螺旋桨装配方法、组装夹具及螺旋桨

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20040066405A (ko) * 2003-01-18 2004-07-27 이중복 병렬 복동식 아일렛 결합장치
CN101629544A (zh) * 2008-07-16 2010-01-20 宜兴市华泰国际集团工业有限公司 风力发电装置桨毂
DE102014206374A1 (de) * 2014-04-03 2015-10-08 Bayerische Motoren Werke Aktiengesellschaft Werkzeug zum Ansetzen eines Drehmomentschlüssels an einer Nietverbindung sowie Vorrichtung und Verfahren zur Bestimmung der Festigkeit einer Nietverbindung
CN105817565A (zh) * 2015-01-06 2016-08-03 北京广振商工汽车部件有限公司 一种角轮铆接装置
CN206464494U (zh) * 2016-12-29 2017-09-05 江苏普华力拓摩擦材料有限公司 一种应用于铆接机的夹具
CN206537504U (zh) * 2017-02-07 2017-10-03 深圳市高巨创新科技开发有限公司 一种便于收纳的螺旋桨组件
CN108127066A (zh) * 2017-12-22 2018-06-08 深圳市道通智能航空技术有限公司 螺旋桨装配方法、组装夹具及螺旋桨

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008153751A2 (en) * 2007-05-25 2008-12-18 Hill Daryl G Conical washer system for propeller stabilization
CN201586725U (zh) * 2010-01-01 2010-09-22 湖北三环离合器有限公司 气动夹具
CA2904575C (en) * 2013-03-14 2022-02-01 Aeryon Labs Inc. Folding propellers system
CN206766327U (zh) * 2017-04-25 2017-12-19 深圳市大疆创新科技有限公司 螺旋桨、动力系统及无人飞行器

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20040066405A (ko) * 2003-01-18 2004-07-27 이중복 병렬 복동식 아일렛 결합장치
CN101629544A (zh) * 2008-07-16 2010-01-20 宜兴市华泰国际集团工业有限公司 风力发电装置桨毂
DE102014206374A1 (de) * 2014-04-03 2015-10-08 Bayerische Motoren Werke Aktiengesellschaft Werkzeug zum Ansetzen eines Drehmomentschlüssels an einer Nietverbindung sowie Vorrichtung und Verfahren zur Bestimmung der Festigkeit einer Nietverbindung
CN105817565A (zh) * 2015-01-06 2016-08-03 北京广振商工汽车部件有限公司 一种角轮铆接装置
CN206464494U (zh) * 2016-12-29 2017-09-05 江苏普华力拓摩擦材料有限公司 一种应用于铆接机的夹具
CN206537504U (zh) * 2017-02-07 2017-10-03 深圳市高巨创新科技开发有限公司 一种便于收纳的螺旋桨组件
CN108127066A (zh) * 2017-12-22 2018-06-08 深圳市道通智能航空技术有限公司 螺旋桨装配方法、组装夹具及螺旋桨

Also Published As

Publication number Publication date
CN108127066A (zh) 2018-06-08
CN108127066B (zh) 2019-06-25

Similar Documents

Publication Publication Date Title
WO2019033769A1 (zh) 折叠螺旋桨、动力组件以及无人飞行器
US20170183081A1 (en) Multi-Rotor Passenger-Carrying Aircraft with Foldable Aircraft Arm
WO2019119877A1 (zh) 折叠螺旋桨、动力组件及无人机
WO2019119940A1 (zh) 螺旋桨装配方法、组装夹具及螺旋桨
CN104443375B (zh) 旋翼叶片和用于将旋翼叶片联接于旋翼毂中的结构系统
US20190367188A1 (en) Bond fixture for leading edge assembly
CN204772181U (zh) 一种胶粘接面剪切强度试验专用夹具
CN103758907B (zh) 无人飞行器的减震装置
US20190241261A1 (en) Bond fixture for composite splice cap assembly
WO2017107751A1 (zh) 无人机
CN110160731B (zh) 用于颤振试验的可调间隙装置
US11584547B2 (en) Fairing bond fixture
WO2019128313A1 (zh) 一种螺旋桨、动力组件及无人机
CN106707461A (zh) 一种轻质反射镜柔性支撑装置
CN110758783A (zh) 一种航天器分离试验装置的扰动力施加机构
JP3169646U (ja) 翼製作ジグ
CN206590116U (zh) 一种折叠桨组件
CN209506081U (zh) 一种拆装快捷的多旋翼无人机机臂结构
WO2017166275A1 (zh) 用于无人飞行器的机架连接组件及无人飞行器
CN116080297A (zh) 可调节角度的驾驶盘图表夹及其使用方法
CN204623857U (zh) 一种飞机平尾快装快卸导向定位销
CN207917146U (zh) 一种螺旋桨、动力组件及无人机
CN206981783U (zh) 一种适用于压缩机轴承装夹的夹紧装置
CN120793200A (zh) 一种辅助支撑接头
CN117601009B (zh) 基于磁流变液的超薄硬脆曲面磨削加工装夹装置及方法

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18892159

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18892159

Country of ref document: EP

Kind code of ref document: A1