WO2022224630A1 - Frame assembly and method for manufacturing same - Google Patents

Frame assembly and method for manufacturing same Download PDF

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Publication number
WO2022224630A1
WO2022224630A1 PCT/JP2022/011413 JP2022011413W WO2022224630A1 WO 2022224630 A1 WO2022224630 A1 WO 2022224630A1 JP 2022011413 W JP2022011413 W JP 2022011413W WO 2022224630 A1 WO2022224630 A1 WO 2022224630A1
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WO
WIPO (PCT)
Prior art keywords
frame assembly
frame
members
assembly according
fixing
Prior art date
Application number
PCT/JP2022/011413
Other languages
French (fr)
Japanese (ja)
Inventor
鈴木陽一
Original Assignee
株式会社エアロネクスト
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 株式会社エアロネクスト filed Critical 株式会社エアロネクスト
Priority to US18/556,855 priority Critical patent/US20240217644A1/en
Priority to JP2023516337A priority patent/JPWO2022224630A1/ja
Priority to CN202210429963.8A priority patent/CN115230935A/en
Priority to CN202220945518.2U priority patent/CN219154730U/en
Publication of WO2022224630A1 publication Critical patent/WO2022224630A1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/70—Constructional aspects of the UAV body

Definitions

  • the present disclosure relates to a frame assembly and a method of manufacturing the frame assembly.
  • flying objects such as drones and unmanned aerial vehicles (UAVs)
  • UAVs unmanned aerial vehicles
  • aircraft fly by connecting equipment, cargo, and the like.
  • sensors such as cameras and microphones are connected.
  • cargo and people are loaded.
  • the flying object and its payloads such as equipment and cargo should fly in a stable state.
  • Patent Document 1 stabilization of the flying object when carrying shooting equipment is attempted (see Patent Document 1).
  • Patent Document 1 cannot eliminate instability due to bending, twisting, etc. of the frame.
  • the present disclosure has been made in view of such a background, and aims to provide a technique capable of stabilizing the frame of an aircraft.
  • the main invention of the present disclosure for solving the above problems is a frame assembly for an aircraft, comprising at least two parallel first frame members extending in a first direction; and a fixing member fixed to each of the first and second frame members.
  • FIG. 4 is a diagram illustrating another configuration example of the frame assembly;
  • FIG. 4 is a diagram illustrating another configuration example of the frame assembly;
  • FIG. 4 is a side view showing an example of a reinforcing method for the frame assembly of the present embodiment;
  • FIG. 4 is a side view showing an example of a reinforcing method for the frame assembly of the present embodiment;
  • FIG. 4 is a side view showing an example of a reinforcing method for the frame assembly of the present embodiment;
  • FIG. 4 is a side view showing an example of a reinforcing method for the frame assembly of the present embodiment;
  • FIG. 4 is a side view showing an example of a reinforcing method for the frame assembly of the present embodiment;
  • FIG. 4 is a side view showing an example of mounting parts connection of the frame assembly of the present embodiment;
  • FIG. 4 is a side view showing an example of mounting parts connection of the frame assembly of the present embodiment;
  • FIG. 4 is a side view showing an example of mounting parts connection of the frame assembly of the present embodiment;
  • FIG. 4 is a side view showing an example of mounting parts connection of the frame assembly of the present embodiment;
  • 1 is a front view of an aircraft using the frame assembly of this embodiment;
  • FIG. FIG. 16 is a top view of the aircraft of FIG. 15;
  • a frame assembly and a frame assembly manufacturing method have the following configuration.
  • (Item 1) A frame assembly for an air vehicle, comprising: at least two parallel first frame members extending in a first direction; a second frame member extending in a second direction perpendicular to the first direction; a fixing member fixed to each of the first and second frame members; with at least one of the fixing members has an opening; frame assembly.
  • (Item 2) A frame assembly according to item 1, wherein: having openings in both of the fixing members, frame assembly.
  • the fixing member is plate-shaped, frame assembly.
  • the reinforcing member is a resin mixed with fibers, frame assembly.
  • the reinforcing member is an adhesive that becomes hard when cured, frame assembly.
  • the reinforcing member is an adhesive that forms an elastic coating when cured, frame assembly.
  • a frame assembly according to either item 6 or 7, The adhesive is a mixture of fibers, frame assembly.
  • a frame assembly according to items 1 to 8, at least one of the two openings comprises a mounting part inside; frame assembly.
  • (Item 10) A frame assembly according to item 9, wherein: The mounting part is a battery case, frame assembly.
  • the mounting part is fixed to one of the two fixing members and provided across the two openings, frame assembly.
  • (Item 12) A frame assembly according to item 9 or 10, The mounting part is fixed to the lower fixing member between the two fixing members and is provided in the opening of the lower fixing member. frame assembly. (Item 13) 13.
  • the frame assembly according to item 11 or 12 The mounting part is inclined with respect to a direction defined by a plane formed by the first frame member and the second frame member and an axis perpendicular to the plane. frame assembly.
  • (Item 14) A method of manufacturing a frame assembly for an aircraft, comprising: securing a securing member to each of at least two parallel first frame members extending in a first direction and second frame members extending in a second direction perpendicular to the first direction; A method of manufacturing a frame assembly.
  • the frame assembly 1 of this embodiment has a structure for fixing fixing members to a plurality of frame members.
  • the material of the frame member is, for example, CFRP (Carbon Fiber Reinforced Plastic).
  • the material of the fixing member can also be CFRP.
  • the rigidity of the frame assembly 1 can be ensured by making the fixing member plate-like and fixing it to a plurality of frame members. Further, the rigidity of the frame assembly 1 may be ensured by passing rod-shaped fixing members as braces between a plurality of frame members.
  • the fixing member can be fixed to the frame member using screws, rivets, etc. (hereinafter collectively referred to as fasteners).
  • fasteners can be arranged at two or more locations on one frame member.
  • the fixing member can be plate-shaped, and the frame member can be sandwiched between two fixing members. Thereby, the rigidity in the vertical direction (the sandwiching direction) of the frame assembly 1 can be ensured.
  • An opening can be provided in one side of the plate-shaped fixing member. As a result, the weight of the frame assembly 1 can be reduced, and various parts can be easily arranged in the opening.
  • FIGS. 1 and 3 are top views of the frame assembly 1 of this embodiment.
  • the frame assembly 1 of the examples of FIGS. 1 and 3 can be used for an aircraft that flies with the direction of arrow D as the forward direction.
  • the frame assembly 1 includes two parallel or substantially parallel frame members 211 and 212 extending in the left-right direction perpendicular to the front-rear direction. At one end of the frame members 211 and 212 , the frame members 221 and 222 extend on the same or substantially the same straight line in the front-rear direction and are parallel or substantially parallel to the frame member 225 .
  • frame members 223 and 224 extend on the same or substantially the same straight line in the front-rear direction and are parallel or substantially parallel to the frame member 226 .
  • frame members 225 and 226 are provided between the frame members 211 and 212 and are spaced apart from the ends of the frame members 213 and 214 and extend parallel or substantially parallel in the front-rear direction.
  • the frame members 213 and 214 may extend from the frame members 225 and 226 toward the outside of the frame assembly 1 on the same or substantially the same straight line in the horizontal direction.
  • the above-mentioned frame members need not necessarily be parallel or approximately parallel, but may extend in parallel. When they are fixed to each other, they are fixed more firmly.
  • Plate-like fixing members 31 and 32 are arranged at the left and right ends of the frame assembly 1 .
  • the fixing member 31 is fixed to the frame members 211 , 212 , 213 , 221 , 222 and 215 by fasteners 40 .
  • the fixing member 31 is fixed to each of the frame members 211, 212, 213, 221, 222, and 215 by fasteners at a plurality of locations.
  • the fixing member 32 is fixed to the frame members 211 , 212 , 214 , 223 , 224 , and 216 at a plurality of locations by fasteners 40 .
  • An opening 11 is formed in the central portion of the frame assembly 1 . Various payloads can be placed in this opening 11 when the frame assembly 1 is used in an aircraft.
  • FIGS. 2 and 4 are top views of the frame assembly 1 of this embodiment.
  • fixing members 33 and 34 are arranged to face the fixing members 31 and 32 of the frame assembly 1 shown in FIG.
  • Frame members 211 , 212 , 213 , 221 , 222 and 225 are sandwiched between fixing members 31 and 33 .
  • fixing members 32 and 34 sandwich frame members 211 , 212 , 223 , 224 , 226 .
  • the fixing member 33 is fixed to each of the frame members 211 , 212 , 213 , 221 , 222 , and 225 at a plurality of locations by fasteners 40 .
  • the fixing member 34 is also fixed to each of the frame members 211 , 212 , 223 , 224 , and 226 at a plurality of locations by fasteners 40 .
  • FIG. 5 is a cross-sectional view taken along line AA of FIGS. 2 and 4.
  • FIG. The fixing members 31 and 33 are shown fixed to the frame member 222 by the fasteners 40 and also fixed to the frame member 213 by the fasteners 40 .
  • the ends of each frame member may be spaced apart from the other frame members, again in the example of FIG.
  • the fixing member 33 is provided with openings 331 and 332 . Therefore, in the top view of FIG. 2, the fixing member 31 can be visually recognized through the openings 331 and 332 .
  • the frame member is also provided with openings 341 and 342 , and the fixing member 32 is visible from above the frame assembly 1 through the openings 341 and 342 .
  • control mechanisms can be arranged in the openings 331, 332, 341, and 342.
  • openings 331, 332, 333, 334, 341, 342, 343, and 344 are provided in the fixing members 31, 32, 33, and . Therefore, as shown in the top view of FIG. 4, the opening is provided to penetrate vertically. As a result, the weight can be reduced compared to the case where the openings are provided only in the fixing members 31 and 33, and devices and parts exceeding the thickness of the frame assembly 1 in the Z-axis direction can be attached to the frame assembly 1. In contrast, it is possible to dispose so as to penetrate in at least one direction.
  • FIG. 6 is a diagram illustrating another configuration example of the frame assembly 1.
  • the fixing member 3 that fixes the plurality of frame members 21 and 22 can be triangular instead of rectangular.
  • the fixing member 3 can be of any shape.
  • the fixing member 3 is fixed to each of the frame members 21 and 22 by fasteners 40 at multiple locations.
  • FIG. 7 is a diagram illustrating another configuration example of the frame assembly 1.
  • FIG. 7 the longitudinal direction of the plurality of frame members 21 and 22 need not be vertical.
  • the fixing member 3 is fixed to each of the frame members 21 and 22 by means of fasteners 40 at a plurality of locations.
  • fasteners 40(P) it is also possible to fix the two frame members 21 and 22 by fasteners 40(P) without providing a gap between the two frame members 21 and 22.
  • the contact area between the frame member and the fixed member becomes narrow like a point or line, which may cause load concentration.
  • a shape e.g., approximately wedge-shaped and having at least one side along the surface of the fixing member when viewed in cross section
  • a reinforcing member 50 having a horizontal shape and at least one other side of which is an arc along the surface of the frame member is further provided, and by performing adhesion, surface connection becomes possible.
  • Materials for the reinforcing member include resin, metal, wood, and the like, but are not limited to these as long as the material has the required strength.
  • the strength can be further increased by mixing short fibers or long fibers (for example, carbon fiber, glass wool, Kevlar, etc.) when molding the reinforcing member 50 parts. is.
  • the adhesive may be of any material or curing method as long as it is generally suitable for adhering adherends (here, materials used for the surfaces of the frame member and the fixing member). For example, drying and solidification, heat curing, chemical reaction and the like can be mentioned.
  • a fibrous material may be mixed with the adhesive to act as a saddle, or the fibrous material 52 may be placed in advance at the adhesive injection site and the adhesive may be injected there to improve the strength. good.
  • the rigidity of the frame assembly is further improved.
  • an adhesive that becomes hard when completely cured for example, epoxy resin, acrylate, etc.
  • an adhesive that forms an elastic film when completely cured for example, silicone resin, modified silicone resin, epoxy resin, acrylic resin, rubber, urethane, etc.
  • silicone resin, modified silicone resin, epoxy resin, acrylic resin, rubber, urethane, etc. avoid touching or dropping the adhesive. In this case, it is possible to have a role of shock absorption.
  • mounting parts such as a battery case, a mechanical plate, and a stay (hereinafter collectively referred to as mounting parts 300) are mounted on the plate-shaped fixing members 31 and 33 that sandwich the frame members, as shown in FIGS. 11 to 14, for example. may be provided. As a result, it becomes easy to arrange various parts and the like by connecting to the fixing member.
  • each mounting part 300 may be the same as that of the fixing members 31 and 33, or may be different. If the mounting part 300 has strength equal to or greater than that of the fixing member, it is possible to prevent the strength of the frame assembly 1 from being lowered or to improve the strength.
  • connection of parts, etc. may be performed by providing a plurality of fixing holes in the fixing member and using fasteners 40, similar to the connection between the frame member and the fixing member.
  • connection method may be any method as long as it can provide the necessary strength, for example, using an adhesive 53 as shown in FIG. 13, or using a method such as welding.
  • the mounting part 300 connected to the fixing member may be connected above or below the fixing member, or may be connected so as to fit in an opening provided in the fixing member.
  • the heavy battery 301 can be provided near the center of the frame assembly in the vertical (Z-axis) direction. It becomes possible. Also, when the mounting part 300 is connected to the opening so as to be fitted in the opening, the area of the opening is reduced, and it is expected that the frame assembly will be prevented from bending or twisting.
  • the mounting part 300 When the mounting part 300 is arranged in the opening, the mounting part may be provided so as to cover the entire opening in a top view, or may be provided so as to cover a part of the opening as shown in FIG. Also, a plurality of mounting parts 300 may be provided in one opening.
  • a flying object 100 illustrated in FIG. 15 flies by rotating a propeller 110 connected to a motor 111 to generate lift. Further, when moving in the horizontal direction or performing an action against the wind, the flying object tilts so that the plane of rotation of the propeller 110 tilts. At this time, if the heavy object is provided at a position far from the center of the aircraft, the aircraft may move slowly.
  • the frame assembly used in the aircraft 100 is configured such that a mounting part 300 (battery case) is connected to the lower fixing member 31 and a battery 301 can be mounted.
  • a mounting part 300 battery case
  • the center of the flying object referred to here is assumed to be the center in any or all of the front, rear, left, and right (X-axis and Y-axis) directions or the vertical (Z-axis) direction.
  • Fixed member 33 is connected to a plurality of frame members, including frame members 229 and 227 .
  • a mounting part 300 such as a battery case is inclined with respect to a plane (XY plane) formed by the frame members 21 and 22 constituting the frame assembly 1 and an axis (Z axis) orthogonal to the plane. may be provided.
  • the two mounting parts 300 are inclined with respect to the Z-axis and provided at an angle that is not parallel to the longitudinal (Y-axis) direction of the aircraft.
  • the mounting part 300 functions as a rectifying plate, so there is no need to add a separate component for rectification, and an increase in the weight of the frame assembly 1 can be suppressed.
  • the direction of inclination of the mounting part 300 is not particularly limited, and for example, it may be inclined in two or more different axial directions. For example, by inclining the mounting part 300 with respect to another axis, it is possible to reduce the influence of the wind on the aircraft from the side. Further, in the frame assembly illustrated in FIG. 15, the mounting part 300 is tilted about the Y-axis in addition to the tilting described above. The interval between the mounting parts 300 in the left-right (X-axis) direction narrows from top to bottom. As a result, the inclined surface of the mounted part 300 can receive the wind from the side of the aircraft 100 .
  • the mounting parts 300 are tilted in two directions, but depending on the shape and application of the aircraft, the tilt rotation axis can be in one direction. Alternatively, two or more directions may be used.
  • a plurality of configurations of the frame assembly in each embodiment can be combined. It is desirable to consider a suitable configuration according to the cost of manufacturing the frame assembly and the environment and characteristics of the location where the frame assembly is operated.
  • Frame assembly Fixing members 21, 22 Frame members 31-34 Fixing member 40 Fastener 50 Reinforcement member, molded part 51 Reinforcement member, adhesive 52 Fibrous material 53 Adhesive 100 Aircraft 110 Propeller 111 Motors 211-216 Frame Members 221 to 230 Frame member 300 Mounting parts 301 Battery

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Abstract

[Problem] To provide a feature with which the frame of an aircraft can be stabilized. [Solution] The main invention of the present invention for solving the above problem is a frame assembly for an aircraft, the frame assembly characterized by comprising at least two parallel first frame members extending in a first direction, a second frame member extending in a second direction perpendicular to the first direction, and fixing members fixed to each of the first and second frame members, at least one of the fixing members having an open part.

Description

フレーム組立体及びフレーム組立体の製造方法Frame assembly and method for manufacturing frame assembly
　本開示は、フレーム組立体及びフレーム組立体の製造方法に関する。 The present disclosure relates to a frame assembly and a method of manufacturing the frame assembly.
　近年、ドローン（Ｄｒｏｎｅ）や無人航空機（ＵＡＶ：Ｕｎｍａｎｎｅｄ　Ａｅｒｉａｌ　Ｖｅｈｉｃｌｅ）などの飛行体（以下、「飛行体」と総称する）を用いた産業の開発が進められている。多くの産業において、飛行体は機材や荷物等を接続して飛行を行う。例えば、撮影、警備、調査、点検などの産業においては、カメラやマイク等のセンサ類を接続する。また、物流や救助等の産業においては、荷物や人などを搭載する。飛行体の産業利用においては、飛行体と、機材や荷物等の搭載物が安定した状態で飛行が行われることが求められる。 In recent years, the development of industries using flying objects (hereinafter collectively referred to as "flying objects") such as drones and unmanned aerial vehicles (UAVs) is progressing. In many industries, aircraft fly by connecting equipment, cargo, and the like. For example, in industries such as photography, security, investigation, and inspection, sensors such as cameras and microphones are connected. In industries such as distribution and rescue, cargo and people are loaded. In the industrial use of flying objects, it is required that the flying object and its payloads such as equipment and cargo should fly in a stable state.
　このような状況を鑑みて、特許文献１においては、撮影機材を搭載する場合などにおける飛行体の安定化が図られている（特許文献１参照）。 In view of this situation, in Patent Document 1, stabilization of the flying object when carrying shooting equipment is attempted (see Patent Document 1).
特開２０１９－１９１５８５号公報JP 2019-191585 A
　しかしながら、特許文献１ではフレームの湾曲や捩れ等による不安定さを解消することができない。 However, Patent Document 1 cannot eliminate instability due to bending, twisting, etc. of the frame.
　本開示はこのような背景を鑑みてなされたものであり、飛行体のフレームを安定させることのできる技術を提供することを目的とする。 The present disclosure has been made in view of such a background, and aims to provide a technique capable of stabilizing the frame of an aircraft.
　上記課題を解決するための本開示の主たる発明は、飛行体用のフレーム組立体であって、少なくとも２つの並行し第１の方向に延在する第１のフレーム部材と、前記第１の方向に垂直な第２の方向に延在する第２のフレーム部材と、前記第１及び第２のフレーム部材のそれぞれに固定される固定部材と、を備えることを特徴とする。　 The main invention of the present disclosure for solving the above problems is a frame assembly for an aircraft, comprising at least two parallel first frame members extending in a first direction; and a fixing member fixed to each of the first and second frame members.　
その他本願が開示する課題やその解決方法については、発明の実施形態の欄及び図面により明らかにされる。 Other problems disclosed by the present application and solutions thereof will be clarified by the section of the embodiment of the invention and the drawings.
　本開示によれば、飛行体のフレームを安定させることができる、フレーム組立体及びフレーム組立体の製造方法を提供し得る。 According to the present disclosure, it is possible to provide a frame assembly and a method of manufacturing the frame assembly that can stabilize the frame of an aircraft.
本実施形態のフレーム組立体の上面図である。It is a top view of the frame assembly of this embodiment. 図１のフレーム組立体の上面図である。Figure 2 is a top view of the frame assembly of Figure 1; 本実施形態のフレーム組立体の上面図である。It is a top view of the frame assembly of this embodiment. 図３のフレーム組立体の上面図である。Figure 4 is a top view of the frame assembly of Figure 3; 図２のＡ－Ａ´断面図である。3 is a cross-sectional view taken along line AA' of FIG. 2; FIG. フレーム組立体における他の構成例を説明する図である。FIG. 4 is a diagram illustrating another configuration example of the frame assembly; フレーム組立体における他の構成例を説明する図である。FIG. 4 is a diagram illustrating another configuration example of the frame assembly; 本実施形態のフレーム組立体の補強方法の例を示す側面図である。FIG. 4 is a side view showing an example of a reinforcing method for the frame assembly of the present embodiment; 本実施形態のフレーム組立体の補強方法の例を示す側面図である。FIG. 4 is a side view showing an example of a reinforcing method for the frame assembly of the present embodiment; 本実施形態のフレーム組立体の補強方法の例を示す側面図である。FIG. 4 is a side view showing an example of a reinforcing method for the frame assembly of the present embodiment; 本実施形態のフレーム組立体の搭載パーツ接続例を示す側面図である。FIG. 4 is a side view showing an example of mounting parts connection of the frame assembly of the present embodiment; 本実施形態のフレーム組立体の搭載パーツ接続例を示す側面図である。FIG. 4 is a side view showing an example of mounting parts connection of the frame assembly of the present embodiment; 本実施形態のフレーム組立体の搭載パーツ接続例を示す側面図である。FIG. 4 is a side view showing an example of mounting parts connection of the frame assembly of the present embodiment; 本実施形態のフレーム組立体の搭載パーツ接続例を示す側面図である。FIG. 4 is a side view showing an example of mounting parts connection of the frame assembly of the present embodiment; 本実施形態のフレーム組立体を用いた飛行体の正面図である。1 is a front view of an aircraft using the frame assembly of this embodiment; FIG. 図１５の飛行体の上面図である。FIG. 16 is a top view of the aircraft of FIG. 15;
　本開示の実施形態の内容を列記して説明する。本開示の実施の形態によるフレーム組立体及びフレーム組立体の製造方法は、以下のような構成を備える。
　（項目１）
　飛行体用のフレーム組立体であって、
　少なくとも２つの並行し第１の方向に延在する第１のフレーム部材と、
　前記第１の方向に垂直な第２の方向に延在する第２のフレーム部材と、
　前記第１及び第２のフレーム部材のそれぞれに固定される固定部材と、
　を備え、
　前記固定部材の少なくとも一方は開口部を有する、
　フレーム組立体。
　（項目２）
　項目１に記載のフレーム組立体であって、
　前記固定部材の両方に開口部を有する、
　フレーム組立体。
　（項目３）
　項目１または２のいずれかに記載のフレーム組立体であって、
　前記固定部材は、板状である、
　フレーム組立体。
　（項目４）
　項目１ないし３のいずれかに記載のフレーム組立体であって、
　前記第１または第２のフレーム部材のいずれかと前記固定部材との双方に密着する形状を有する補強部材をさらに備える、
　フレーム組立体。
　（項目５）
　項目４に記載のフレーム組立体であって、
　前記補強部材は、繊維を混ぜた樹脂である、
　フレーム組立体。
　（項目６）
　項目４に記載のフレーム組立体であって、
　前記補強部材は、硬化時に硬質となる接着剤である、
　フレーム組立体。
　（項目７）
　項目４に記載のフレーム組立体であって、
　前記補強部材は、硬化時に弾力性のある被膜を形成する接着剤である、
　フレーム組立体。
　（項目８）
　項目６または７のいずれかに記載のフレーム組立体であって、
　前記接着剤は、繊維を混ぜたものである、
　フレーム組立体。
　（項目９）
　項目１ないし８に記載のフレーム組立体であって、
　２つの前記開口部の少なくとも一方は、内部に搭載パーツを備える、
　フレーム組立体。
　（項目１０）
　項目９に記載のフレーム組立体であって、
　前記搭載パーツは、バッテリーケースである、
　フレーム組立体。
　（項目１１）
　項目９または１０に記載のフレーム組立体であって、
　前記搭載パーツは、２つの前記固定部材の一方に固定され、２つの前記開口部内に跨って備えられる、
　フレーム組立体。
　（項目１２）
　項目９または１０に記載のフレーム組立体であって、
　前記搭載パーツは、２つの前記固定部材の間であって、下側の固定部材に固定され、前記下側の固定部材の開口部内に備えられる、
　フレーム組立体。
　（項目１３）
　項目１１または１２に記載のフレーム組立体であって、
　前記搭載パーツは、前記第１のフレーム部材と、前記第２のフレーム部材とからなる面および該面を直交する軸により規定される方向に対して傾斜して設けられる、
　フレーム組立体。
　（項目１４）
　飛行体用のフレーム組立体の製造方法であって、
　少なくとも２つの並行し第１の方向に延在する第１のフレーム部材と、前記第１の方向に垂直な第２の方向に延在する第２のフレーム部材のそれぞれに固定部材を固定する、
　フレーム組立体の製造方法。 The contents of the embodiments of the present disclosure are listed and described. A frame assembly and a frame assembly manufacturing method according to an embodiment of the present disclosure have the following configuration.
(Item 1)
A frame assembly for an air vehicle, comprising:
at least two parallel first frame members extending in a first direction;
a second frame member extending in a second direction perpendicular to the first direction;
a fixing member fixed to each of the first and second frame members;
with
at least one of the fixing members has an opening;
frame assembly.
(Item 2)
A frame assembly according to item 1, wherein:
having openings in both of the fixing members,
frame assembly.
(Item 3)
A frame assembly according to either item 1 or 2,
The fixing member is plate-shaped,
frame assembly.
(Item 4)
A frame assembly according to any one of items 1 to 3,
further comprising a reinforcing member having a shape that adheres to both the first or second frame member and the fixing member;
frame assembly.
(Item 5)
A frame assembly according to item 4,
The reinforcing member is a resin mixed with fibers,
frame assembly.
(Item 6)
A frame assembly according to item 4,
The reinforcing member is an adhesive that becomes hard when cured,
frame assembly.
(Item 7)
A frame assembly according to item 4,
The reinforcing member is an adhesive that forms an elastic coating when cured,
frame assembly.
(Item 8)
A frame assembly according to either item 6 or 7,
The adhesive is a mixture of fibers,
frame assembly.
(Item 9)
A frame assembly according to items 1 to 8,
at least one of the two openings comprises a mounting part inside;
frame assembly.
(Item 10)
A frame assembly according to item 9, wherein:
The mounting part is a battery case,
frame assembly.
(Item 11)
A frame assembly according to item 9 or 10,
The mounting part is fixed to one of the two fixing members and provided across the two openings,
frame assembly.
(Item 12)
A frame assembly according to item 9 or 10,
The mounting part is fixed to the lower fixing member between the two fixing members and is provided in the opening of the lower fixing member.
frame assembly.
(Item 13)
13. The frame assembly according to item 11 or 12,
The mounting part is inclined with respect to a direction defined by a plane formed by the first frame member and the second frame member and an axis perpendicular to the plane.
frame assembly.
(Item 14)
A method of manufacturing a frame assembly for an aircraft, comprising:
securing a securing member to each of at least two parallel first frame members extending in a first direction and second frame members extending in a second direction perpendicular to the first direction;
A method of manufacturing a frame assembly.
＜フレーム組立体１の第一の実施の形態の概要＞
　以下、本開示の一実施形態に係る飛行体用のフレーム組立体１について説明する。本実施形態のフレーム組立体１は、複数のフレーム部材に固定部材を固定する構造を備える。 <Overview of First Embodiment of Frame Assembly 1>
A frame assembly 1 for an aircraft according to an embodiment of the present disclosure will be described below. The frame assembly 1 of this embodiment has a structure for fixing fixing members to a plurality of frame members.
　フレーム部材の素材は、例えば、ＣＦＲＰ（Carbon Fiber Reinforced Plastic；炭素繊維強化プラスチック）である。固定部材の素材も同様にＣＦＲＰとすることができる。固定部材を板状にし、複数のフレーム部材と固定することによりフレーム組立体１の剛性を確保することができる。また、棒状の固定部材を筋交いとして複数のフレーム部材の間に渡すことによりフレーム組立体１の剛性を確保するようにしてもよい。 The material of the frame member is, for example, CFRP (Carbon Fiber Reinforced Plastic). The material of the fixing member can also be CFRP. The rigidity of the frame assembly 1 can be ensured by making the fixing member plate-like and fixing it to a plurality of frame members. Further, the rigidity of the frame assembly 1 may be ensured by passing rod-shaped fixing members as braces between a plurality of frame members.
　また、固定部材はフレーム部材にねじやリベット等（以下、固着具と総称する）を用いて止めることができる。これによりクランプ等の機構を省略することが可能となり、フレーム組立体１の軽量化を図ることができる。固着具は１つのフレーム部材について２箇所以上配置することができる。 In addition, the fixing member can be fixed to the frame member using screws, rivets, etc. (hereinafter collectively referred to as fasteners). As a result, a mechanism such as a clamp can be omitted, and the weight of the frame assembly 1 can be reduced. The fasteners can be arranged at two or more locations on one frame member.
　また、固定部材を板状にし、２枚の固定部材によりフレーム部材を挟持させることができる。これによりフレーム組立体１の上下方向（挟持する方向）への剛性を確保することができる。板状の固定部材の一方には開口を設けることができる。これによりフレーム組立体１の軽量化を図り、また開口内に各種の部品等を配置することが容易となる。 Also, the fixing member can be plate-shaped, and the frame member can be sandwiched between two fixing members. Thereby, the rigidity in the vertical direction (the sandwiching direction) of the frame assembly 1 can be ensured. An opening can be provided in one side of the plate-shaped fixing member. As a result, the weight of the frame assembly 1 can be reduced, and various parts can be easily arranged in the opening.
＜フレーム組立体１の第一の実施の形態の構成＞
　図１及び図３は、本実施形態のフレーム組立体１の上面図である。図１及び図３の例のフレーム組立体１は、矢印Ｄの方向を前方向として飛行する飛行体に用いることができる。フレーム組立体１は、前後方向に垂直な左右方向に延在する２本の平行または略平行で並行するフレーム部材２１１及び２１２を備える。フレーム部材２１１及び２１２の一方の端部には、前後方向に同一または略同一の直線上にフレーム部材２２１及び２２２が延在し、フレーム部材２２５に対して平行または略平行で並行する。フレーム部材２１１及び２１２の他方の端部には、前後方向に同一または略同一の直線上にフレーム部材２２３及び２２４が延在し、フレーム部材２２６に対して平行または略平行で並行する。また、フレーム部材２１１及び２１２の間においてフレーム部材２１３または２１４の端部から離間して前後方向に平行または略平行で並行するように延在するフレーム部材２２５及び２２６が設けられる。また、フレーム部材２２５及び２２６からそれぞれフレーム組立体１の外側に向けて左右方向に同一または略同一の直線上にフレーム部材２１３及び２１４が延在するようにしてもよい。なお、上述のフレーム部材同士は、必ずしも平行または略平行でなくても並行に延在していればよいが、平行であるフレーム部材に対して垂直なフレーム部材が後述の固定部材３１及び３２により互いに固定されていると、より強固に固定される。 <Configuration of First Embodiment of Frame Assembly 1>
1 and 3 are top views of the frame assembly 1 of this embodiment. The frame assembly 1 of the examples of FIGS. 1 and 3 can be used for an aircraft that flies with the direction of arrow D as the forward direction. The frame assembly 1 includes two parallel or substantially parallel frame members 211 and 212 extending in the left-right direction perpendicular to the front-rear direction. At one end of the frame members 211 and 212 , the frame members 221 and 222 extend on the same or substantially the same straight line in the front-rear direction and are parallel or substantially parallel to the frame member 225 . At the other ends of the frame members 211 and 212 , frame members 223 and 224 extend on the same or substantially the same straight line in the front-rear direction and are parallel or substantially parallel to the frame member 226 . Further, frame members 225 and 226 are provided between the frame members 211 and 212 and are spaced apart from the ends of the frame members 213 and 214 and extend parallel or substantially parallel in the front-rear direction. Alternatively, the frame members 213 and 214 may extend from the frame members 225 and 226 toward the outside of the frame assembly 1 on the same or substantially the same straight line in the horizontal direction. The above-mentioned frame members need not necessarily be parallel or approximately parallel, but may extend in parallel. When they are fixed to each other, they are fixed more firmly.
　フレーム組立体１の左右端部には板状の固定部材３１及び３２が配される。固定部材３１は、固着具４０により、フレーム部材２１１、２１２、２１３、２２１、２２２、２１５にそれぞれ固定される。固定部材３１は、フレーム部材２１１、２１２、２１３、２２１、２２２、２１５にそれぞれ複数箇所固着具により固定される。同様に、固定部材３２は、固着具４０により、フレーム部材２１１、２１２、２１４、２２３、２２４、２１６にそれぞれ複数箇所で固定される。フレーム組立体１の中央部には開口１１が形成される。フレーム組立体１が飛行体に用いられた場合、この開口部１１には各種のペイロードを配置することができる。 Plate- like fixing members 31 and 32 are arranged at the left and right ends of the frame assembly 1 . The fixing member 31 is fixed to the frame members 211 , 212 , 213 , 221 , 222 and 215 by fasteners 40 . The fixing member 31 is fixed to each of the frame members 211, 212, 213, 221, 222, and 215 by fasteners at a plurality of locations. Similarly, the fixing member 32 is fixed to the frame members 211 , 212 , 214 , 223 , 224 , and 216 at a plurality of locations by fasteners 40 . An opening 11 is formed in the central portion of the frame assembly 1 . Various payloads can be placed in this opening 11 when the frame assembly 1 is used in an aircraft.
　図２及び図４は、本実施形態のフレーム組立体１の上面図である。図２及び図４の例では、図１に示すフレーム組立体１の固定部材３１及び３２に対抗させてさらに固定部材３３及び３４を配置している。固定部材３１及び３３により、フレーム部材２１１、２１２、２１３、２２１、２２２、２２５がサンドイッチされる。同様に、固定部材３２及び３４により、フレーム部材２１１、２１２、２２３、２２４、２２６がサンドイッチされる。固定部材３３は、固着具４０により、フレーム部材２１１、２１２、２１３、２２１、２２２、２２５のそれぞれと複数箇所固定される。同様に固定部材３４も、固着具４０により、フレーム部材２１１、２１２、２２３、２２４、２２６のそれぞれと複数箇所固定される。 2 and 4 are top views of the frame assembly 1 of this embodiment. In the examples of FIGS. 2 and 4, fixing members 33 and 34 are arranged to face the fixing members 31 and 32 of the frame assembly 1 shown in FIG. Frame members 211 , 212 , 213 , 221 , 222 and 225 are sandwiched between fixing members 31 and 33 . Similarly, fixing members 32 and 34 sandwich frame members 211 , 212 , 223 , 224 , 226 . The fixing member 33 is fixed to each of the frame members 211 , 212 , 213 , 221 , 222 , and 225 at a plurality of locations by fasteners 40 . Similarly, the fixing member 34 is also fixed to each of the frame members 211 , 212 , 223 , 224 , and 226 at a plurality of locations by fasteners 40 .
　図５は、図２及び図４のＡ－Ａ断面図である。固定部材３１及び３３は、フレーム部材２２２に固着具４０により固定されるとともに、フレーム部材２１３にも固着具４０により固定されている様子が示されている。各フレーム部材の端部は他のフレーム部材から離間していてよく、図３の例でも、フレーム部材２２２の端部２２２１とフレーム部材２１３との間に間隙１２が設けられている。 FIG. 5 is a cross-sectional view taken along line AA of FIGS. 2 and 4. FIG. The fixing members 31 and 33 are shown fixed to the frame member 222 by the fasteners 40 and also fixed to the frame member 213 by the fasteners 40 . The ends of each frame member may be spaced apart from the other frame members, again in the example of FIG.
　図２に戻り、固定部材３３には開口部３３１及び３３２が設けられる。したがって、図２の上面図では、開口部３３１及び３３２からは固定部材３１が視認可能となる。同様に、フレーム部材にも開口部３４１及び３４２が設けられ、フレーム組立体１の上方からは開口部３４１及び３４２を通って固定部材３２が視認可能となる。フレーム組立体１が飛行体に用いられた場合、開口部３３１、３３２、３４１、３４２には、例えば、制御機構などを配置することが可能となる。 Returning to FIG. 2, the fixing member 33 is provided with openings 331 and 332 . Therefore, in the top view of FIG. 2, the fixing member 31 can be visually recognized through the openings 331 and 332 . Similarly, the frame member is also provided with openings 341 and 342 , and the fixing member 32 is visible from above the frame assembly 1 through the openings 341 and 342 . When the frame assembly 1 is used in an aircraft, for example, control mechanisms can be arranged in the openings 331, 332, 341, and 342.
　また、図３及び図４の構成例においては、固定部材３１、３２、３３、３４に開口部３３１、３３２、３３３、３３４、３４１、３４２、３４３、３４４が設けられる。したがって、図４の上面図に示されるように、開口部は上下に貫通して設けられる。これにより、固定部材３１及び３３のみに開口部を設けた場合に比較して軽量化が可能となるほか、フレーム組立体１のＺ軸方向における厚みを超える機器やパーツを、フレーム組立体１に対して少なくとも１方向に貫通させて配置することが可能となる。 3 and 4, openings 331, 332, 333, 334, 341, 342, 343, and 344 are provided in the fixing members 31, 32, 33, and . Therefore, as shown in the top view of FIG. 4, the opening is provided to penetrate vertically. As a result, the weight can be reduced compared to the case where the openings are provided only in the fixing members 31 and 33, and devices and parts exceeding the thickness of the frame assembly 1 in the Z-axis direction can be attached to the frame assembly 1. In contrast, it is possible to dispose so as to penetrate in at least one direction.
　図６は、フレーム組立体１における他の構成例を説明する図である。図６に示すように、複数のフレーム部材２１及び２２を固定する固定部材３は、矩形ではなく三角形とすることができる。また、固定部材３は任意の形状とすることができる。ここでも固定部材３は、固着具４０によりフレーム部材２１及び２２のそれぞれと複数箇所固着具により固定される。 FIG. 6 is a diagram illustrating another configuration example of the frame assembly 1. FIG. As shown in FIG. 6, the fixing member 3 that fixes the plurality of frame members 21 and 22 can be triangular instead of rectangular. Moreover, the fixing member 3 can be of any shape. Here, too, the fixing member 3 is fixed to each of the frame members 21 and 22 by fasteners 40 at multiple locations.
　図７は、フレーム組立体１における他の構成例を説明する図である。図７に示すように、複数のフレーム部材２１及び２２の長手方向の方向は垂直でなくてもよい。図７の例でも、固定部材３は、フレーム部材２１及び２２のそれぞれと固着具４０により複数箇所固定される。図７に示すように、２つのフレーム部材２１及び２２の間に間隙を設けず、２つのフレーム部材２１及び２２を固着具４０（Ｐ）により固定することも可能である。図１、図２に示すフレーム組立体１においても、一部または全部のフレーム部材の端部を他のフレーム部材に固定するようにしてよい。 FIG. 7 is a diagram illustrating another configuration example of the frame assembly 1. FIG. As shown in FIG. 7, the longitudinal direction of the plurality of frame members 21 and 22 need not be vertical. In the example of FIG. 7 as well, the fixing member 3 is fixed to each of the frame members 21 and 22 by means of fasteners 40 at a plurality of locations. As shown in FIG. 7, it is also possible to fix the two frame members 21 and 22 by fasteners 40(P) without providing a gap between the two frame members 21 and 22. FIG. Also in the frame assembly 1 shown in FIGS. 1 and 2, the ends of some or all of the frame members may be fixed to other frame members.
　フレーム部材と固定部材とを、固着具によって接続した場合、フレーム部材と固定部材が接する面積が点や線のように狭くなるため、負荷の集中が起こる場合がある。繰り返し負荷がかかる用途に用いる場合には、耐久性を向上させるため、フレーム部材と固定部材が接する面積を拡大させ、負荷を分散させることが望ましい。 When the frame member and the fixed member are connected by a fastener, the contact area between the frame member and the fixed member becomes narrow like a point or line, which may cause load concentration. When used in applications where repeated loads are applied, it is desirable to increase the contact area between the frame member and the fixing member to distribute the load in order to improve durability.
　図８及び図９に例示されるように、フレーム部材と固定部材の双方に密着する形状（例えば、略楔形であって、断面形状を見たとき、少なくとも一辺は固定部材の表面に沿うように水平であり、その他の少なくとも一辺はフレーム部材の表面に沿う弧である形状）の補強部材５０をさらに備え、接着を行うことにより、面による接続が可能となる。補強部材の素材は、樹脂や金属、木等が挙げられるが、必要な強度を備えている素材であればこれに限らない。また、樹脂を素材とする補強部材５０を用いる場合には、補強部材５０パーツ成形時に、短繊維又は長繊維（例えば、炭素繊維、グラスウール、ケプラー等）を混ぜることで更に強度を高めることが可能である。 As exemplified in FIGS. 8 and 9, a shape (e.g., approximately wedge-shaped and having at least one side along the surface of the fixing member when viewed in cross section) is in close contact with both the frame member and the fixing member. A reinforcing member 50 having a horizontal shape and at least one other side of which is an arc along the surface of the frame member is further provided, and by performing adhesion, surface connection becomes possible. Materials for the reinforcing member include resin, metal, wood, and the like, but are not limited to these as long as the material has the required strength. In addition, when using the reinforcing member 50 made of resin, the strength can be further increased by mixing short fibers or long fibers (for example, carbon fiber, glass wool, Kevlar, etc.) when molding the reinforcing member 50 parts. is.
　補強部材は、樹脂等を予め成形したパーツを用いる他に、図１０に例示するように接着剤を塗布し、接着剤の硬化により形成されたパーツを補強部材５１とする方法がある。接着剤は、一般に被着材（ここでは、フレーム部材と固定部材の表面に用いられる素材）の接着に適するものであれば素材や硬化方法を問わない。例えば、乾燥固化、熱硬化、化学反応等が挙げられる。また、接着剤に繊維状材料を混ぜ、すさの役割を持たせたり、接着剤の注入箇所に予め繊維状材料５２を置き、そこに接着剤を注入して強度を向上させたりするものとしてもよい。 In addition to using pre-molded parts of resin or the like as reinforcing members, there is also a method of applying an adhesive as shown in FIG. The adhesive may be of any material or curing method as long as it is generally suitable for adhering adherends (here, materials used for the surfaces of the frame member and the fixing member). For example, drying and solidification, heat curing, chemical reaction and the like can be mentioned. Alternatively, a fibrous material may be mixed with the adhesive to act as a saddle, or the fibrous material 52 may be placed in advance at the adhesive injection site and the adhesive may be injected there to improve the strength. good.
　完全硬化時に硬質となる接着剤（例えば、エポキシ樹脂系、アクリレート系等）を用いる場合には、フレーム組立体の剛性が更に向上する。また、完全硬化時に弾性のある被膜を形成する接着剤（例えば、シリコーン樹脂系、変成シリコーン樹脂系、エポキシ樹脂系、アクリル樹脂系、ゴム系、ウレタン系等）を用いる場合には、接触や落下の際、衝撃吸収の役割を持たせることが可能となる。 When using an adhesive that becomes hard when completely cured (for example, epoxy resin, acrylate, etc.), the rigidity of the frame assembly is further improved. Also, when using an adhesive that forms an elastic film when completely cured (for example, silicone resin, modified silicone resin, epoxy resin, acrylic resin, rubber, urethane, etc.), avoid touching or dropping the adhesive. In this case, it is possible to have a role of shock absorption.
＜フレーム組立体１の第二の実施の形態の概要＞
　以下、本開示によるフレーム組立体の第二の実施の形態の詳細において、フレーム組立体１の第一の実施の形態と重複する構成要素は同様とすることができるため、再度の説明は省略する。 <Overview of Second Embodiment of Frame Assembly 1>
In the following, in the details of the second embodiment of the frame assembly according to the present disclosure, the same components as those of the first embodiment of the frame assembly 1 can be used, and therefore repeated descriptions will be omitted. .
＜フレーム組立体１の第二の実施の形態の構成＞
　フレーム部材を挟持する板状の固定部材３１、３３には、例えば、図１１－図１４に示されるように、バッテリーケースやメカプレート、ステー等の搭載パーツ（以下、搭載パーツ３００と総称する）を設けてもよい。これにより、固定部材に接続して各種の部品等を配置することが容易となる。 <Configuration of Second Embodiment of Frame Assembly 1>
Mounting parts such as a battery case, a mechanical plate, and a stay (hereinafter collectively referred to as mounting parts 300) are mounted on the plate-shaped fixing members 31 and 33 that sandwich the frame members, as shown in FIGS. 11 to 14, for example. may be provided. As a result, it becomes easy to arrange various parts and the like by connecting to the fixing member.
　各搭載パーツ３００の素材は、固定部材３１、３３と同じ素材でも良いし、異なる素材でもよい。搭載パーツ３００に固定部材と同等またはそれ以上の強度を持たせた場合、フレーム組立体１の強度の低下を防ぐまたは強度を向上させることが出来る。 The material of each mounting part 300 may be the same as that of the fixing members 31 and 33, or may be different. If the mounting part 300 has strength equal to or greater than that of the fixing member, it is possible to prevent the strength of the frame assembly 1 from being lowered or to improve the strength.
　部品等の接続は、フレーム部材と固定部材との接続と同様に、固定部材に固定用の穴を複数設け、固着具４０を用いることとしても良い。また、接続方法は、必要な強度を持たせることができる方法であればよく、例えば、図１３に示されるように接着材５３を用いたり、溶着等の手法を用いたりしてもよい。 The connection of parts, etc., may be performed by providing a plurality of fixing holes in the fixing member and using fasteners 40, similar to the connection between the frame member and the fixing member. Moreover, the connection method may be any method as long as it can provide the necessary strength, for example, using an adhesive 53 as shown in FIG. 13, or using a method such as welding.
　固定部材に接続する搭載パーツ３００は、固定部材の上方や下方に接続しても良いし、固定部材に設けた開口部内に嵌まるように接続しても良い。例えば、図１５及び図１６に示されるように、バッテリーケースを開口部に嵌めて接続することで、重量物であるバッテリー３０１を上下（Ｚ軸）方向におけるフレーム組立体の中心付近に設けることが可能となる。また、搭載パーツ３００を開口部に開口部内に嵌まるように接続する場合、開口面積が減少し、フレーム組み立体の湾曲や捩れの防止が期待できる。 The mounting part 300 connected to the fixing member may be connected above or below the fixing member, or may be connected so as to fit in an opening provided in the fixing member. For example, as shown in FIGS. 15 and 16, by fitting and connecting the battery case to the opening, the heavy battery 301 can be provided near the center of the frame assembly in the vertical (Z-axis) direction. It becomes possible. Also, when the mounting part 300 is connected to the opening so as to be fitted in the opening, the area of the opening is reduced, and it is expected that the frame assembly will be prevented from bending or twisting.
　開口部内に搭載パーツ３００を配置する場合、搭載パーツは上面視において開口部を全て塞ぐように設けても良いし、図１１のように開口部の一部を塞ぐように設けても良い。また、一つの開口部内に複数の搭載パーツ３００を設けても良い。 When the mounting part 300 is arranged in the opening, the mounting part may be provided so as to cover the entire opening in a top view, or may be provided so as to cover a part of the opening as shown in FIG. Also, a plurality of mounting parts 300 may be provided in one opening.
　図１５に例示される飛行体１００は、モータ１１１に接続されたプロペラ１１０が回転し、揚力を生むことで飛行を行う。また、水平方向への移動や、風に対抗する動作を行う場合には、プロペラ１１０の回転面が傾くように飛行体が傾斜する。このとき、重量物が飛行体の中心から遠い位置に設けられていると、飛行体の動作が緩慢となる場合がある。 A flying object 100 illustrated in FIG. 15 flies by rotating a propeller 110 connected to a motor 111 to generate lift. Further, when moving in the horizontal direction or performing an action against the wind, the flying object tilts so that the plane of rotation of the propeller 110 tilts. At this time, if the heavy object is provided at a position far from the center of the aircraft, the aircraft may move slowly.
　飛行体１００に用いられるフレーム組立体は、図１４に例示されるように、下側の固定部材３１に搭載パーツ３００（バッテリーケース）を接続し、バッテリー３０１が搭載可能となるように構成されている。バッテリー３０１や搭載する荷物等の重量物を飛行体中心付近に集めることでマスが集中し、反応速度や安定性の向上が期待できる。ここで言う飛行体中心とは、前後左右（Ｘ軸及びＹ軸）方向又は、上下（Ｚ軸）方向のいずれか又は全ての軸においての中心が想定される。固定部材３３は、フレーム部材２２９、２２７を含む複数のフレーム部材に接続されている。 As illustrated in FIG. 14, the frame assembly used in the aircraft 100 is configured such that a mounting part 300 (battery case) is connected to the lower fixing member 31 and a battery 301 can be mounted. there is By gathering heavy objects such as the battery 301 and cargo to be loaded near the center of the aircraft, mass is concentrated, and an improvement in reaction speed and stability can be expected. The center of the flying object referred to here is assumed to be the center in any or all of the front, rear, left, and right (X-axis and Y-axis) directions or the vertical (Z-axis) direction. Fixed member 33 is connected to a plurality of frame members, including frame members 229 and 227 .
　マスの集中を目的とする場合だけでなく、固定部材の任意の位置に開口部を設けてパーツを搭載できるようにすることで、各パーツを飛行体の最適な位置に設けることが容易となり、設計の自由度が向上する。 Not only for the purpose of mass concentration, by providing an opening at any position on the fixed member so that parts can be mounted, it becomes easy to install each part at the optimal position of the aircraft. The degree of freedom in design is improved.
　バッテリーケース等の搭載パーツ３００は、フレーム組立体１を構成するフレーム部材２１、２２からなる面（ＸＹ平面）および該面に直交する軸（Ｚ軸）を基準とする方向に対して傾斜させて設けてもよい。例えば、図１５及び図１６に例示されるフレーム組立体では、２個の搭載パーツ３００が、Ｚ軸に対して傾斜し、飛行体の前後（Ｙ軸）方向に対して平行しない角度で設けている。飛行体１００の後方（正のＹ軸方向）へ向かって、２個の搭載パーツ３００の間隔を狭くすることで、例えば、飛行体１００の下部において、飛行体１００の前方から後方に向かう気流を整えることもできる。また、例えば、飛行体１００の周囲（特に、飛行体１００の下方）を流れる気流の乱れが減少することで、意図しない気流によるフレームのねじれが抑制されたり、飛行体１００の飛行効率が向上しうる。また、搭載パーツ３００が整流板としての役割を発揮し、別途整流のための部品を追加する必要がなく、フレーム組立体１の重量の増加を抑制できる。 A mounting part 300 such as a battery case is inclined with respect to a plane (XY plane) formed by the frame members 21 and 22 constituting the frame assembly 1 and an axis (Z axis) orthogonal to the plane. may be provided. For example, in the frame assembly illustrated in FIGS. 15 and 16, the two mounting parts 300 are inclined with respect to the Z-axis and provided at an angle that is not parallel to the longitudinal (Y-axis) direction of the aircraft. there is By narrowing the distance between the two mounting parts 300 toward the rear (positive Y-axis direction) of the flying object 100, for example, in the lower part of the flying object 100, airflow from the front to the rear of the flying object 100 can be reduced. can also be arranged. In addition, for example, by reducing the turbulence of the airflow flowing around the flying object 100 (especially below the flying object 100), twisting of the frame due to unintended airflow can be suppressed, and the flight efficiency of the flying object 100 can be improved. sell. In addition, the mounting part 300 functions as a rectifying plate, so there is no need to add a separate component for rectification, and an increase in the weight of the frame assembly 1 can be suppressed.
　なお、搭載パーツ３００の傾斜の方向は特に限定されず、例えば、異なる二軸方向以上に傾斜してもよい。例えば、他の軸に対して搭載パーツ３００を傾斜させることによって、飛行体が側方から風を受けた際の影響を低減させることができる。また、図１５に例示されるフレーム組立体では、搭載パーツ３００は、前述の傾斜に加えて、Ｙ軸を回転に軸として傾斜している。左右（Ｘ軸）方向における搭載パーツ３００同士の間隔が、上方から下方に向かって狭くなっている。これにより、飛行体１００の側方からの風を、搭載パーツ３００の傾斜した面で受けることが可能となる。すなわち、上方と下方でバッテリーケースの間隔が変わらないよう平行に設けられた場合に比較して、フレーム組立体１が側面方向から押される力が低減されるため、意図しない飛行体１００の姿勢の崩れを抑えることができる。なお、図１５及び図１６において例示されるフレーム組立体１では、搭載パーツ３００が２方向の傾斜を行っているが、飛行体の形状や用途により、傾斜の回転軸となる方向は１方向でもよいし、２方向以上でもよい。 The direction of inclination of the mounting part 300 is not particularly limited, and for example, it may be inclined in two or more different axial directions. For example, by inclining the mounting part 300 with respect to another axis, it is possible to reduce the influence of the wind on the aircraft from the side. Further, in the frame assembly illustrated in FIG. 15, the mounting part 300 is tilted about the Y-axis in addition to the tilting described above. The interval between the mounting parts 300 in the left-right (X-axis) direction narrows from top to bottom. As a result, the inclined surface of the mounted part 300 can receive the wind from the side of the aircraft 100 . That is, compared to the case where the upper and lower battery cases are arranged in parallel so that the interval between the battery cases does not change, the force pushing the frame assembly 1 from the side direction is reduced. collapse can be suppressed. In the frame assembly 1 illustrated in FIGS. 15 and 16, the mounting parts 300 are tilted in two directions, but depending on the shape and application of the aircraft, the tilt rotation axis can be in one direction. Alternatively, two or more directions may be used.
　各実施の形態におけるフレーム組立体の構成は、複数を組み合わせて実施することが可能である。フレーム組立体の製造におけるコストや、フレーム組立体が運用される場所の環境や特性に合わせて、適宜好適な構成を検討することが望ましい。 A plurality of configurations of the frame assembly in each embodiment can be combined. It is desirable to consider a suitable configuration according to the cost of manufacturing the frame assembly and the environment and characteristics of the location where the frame assembly is operated.
　上述した実施の形態は、本技術の理解を容易にするための例示に過ぎず、本発明を限定して解釈するためのものではない。本発明は、その趣旨を逸脱することなく、変更、改良することができると共に、本発明にはその均等物が含まれることは言うまでもない。 The above-described embodiments are merely examples for facilitating understanding of the present technology, and are not intended to limit and interpret the present invention. It goes without saying that the present invention can be modified and improved without departing from its spirit, and that equivalents thereof are included in the present invention.
１　　　　フレーム組立体
３　　　　固定部材
２１、２２　　フレーム部材
３１～３４　　固定部材
４０　　　固着具
５０　　　補強部材、成形パーツ
５１　　　補強部材、接着剤
５２　　　繊維状材料
５３　　　接着剤
１００　　飛行体
１１０　　プロペラ
１１１　　モータ
２１１～２１６　　フレーム部材
２２１～２３０　　フレーム部材
３００　　搭載パーツ
３０１　　バッテリー

 
  1 Frame assembly 3 Fixing members 21, 22 Frame members 31-34 Fixing member 40 Fastener 50 Reinforcement member, molded part 51 Reinforcement member, adhesive 52 Fibrous material 53 Adhesive 100 Aircraft 110 Propeller 111 Motors 211-216 Frame Members 221 to 230 Frame member 300 Mounting parts 301 Battery

Claims (14)

  1. 　飛行体用のフレーム組立体であって、
    　少なくとも２つの並行し第１の方向に延在する第１のフレーム部材と、
    　前記第１の方向に垂直な第２の方向に延在する第２のフレーム部材と、
    　前記第１及び第２のフレーム部材のそれぞれに固定される固定部材と、
    　を備え、
    　前記固定部材の少なくとも一方は開口部を有する、
    　フレーム組立体。     A frame assembly for an air vehicle, comprising:
    at least two parallel first frame members extending in a first direction;
    a second frame member extending in a second direction perpendicular to the first direction;
    a fixing member fixed to each of the first and second frame members;
    with
    at least one of the fixing members has an opening;
    frame assembly.
  2. 　請求項１に記載のフレーム組立体であって、
    　前記固定部材の両方に開口部を有する、
    　フレーム組立体。     A frame assembly according to claim 1, comprising:
    having openings in both of the fixing members,
    frame assembly.
  3. 　請求項１または２のいずれかに記載のフレーム組立体であって、
    　前記固定部材は、板状である、
    　フレーム組立体。     A frame assembly according to any one of claims 1 or 2,
    The fixing member is plate-shaped,
    frame assembly.
  4. 　請求項１ないし３のいずれかに記載のフレーム組立体であって、
    　前記第１または第２のフレーム部材のいずれかと前記固定部材との双方に密着する形状を有する補強部材をさらに備える、
    　フレーム組立体。     A frame assembly according to any one of claims 1 to 3,
    further comprising a reinforcing member having a shape that adheres to both the first or second frame member and the fixing member;
    frame assembly.
  5. 　請求項４に記載のフレーム組立体であって、
    　前記補強部材は、繊維を混ぜた樹脂である、
    　フレーム組立体。     A frame assembly according to claim 4, comprising:
    The reinforcing member is a resin mixed with fibers,
    frame assembly.
  6. 　請求項４に記載のフレーム組立体であって、
    　前記補強部材は、硬化時に硬質となる接着剤である、
    　フレーム組立体。     A frame assembly according to claim 4, comprising:
    The reinforcing member is an adhesive that becomes hard when cured,
    frame assembly.
  7. 　請求項４に記載のフレーム組立体であって、
    　前記補強部材は、硬化時に弾力性のある被膜を形成する接着剤である、
    　フレーム組立体。     A frame assembly according to claim 4, comprising:
    The reinforcing member is an adhesive that forms an elastic coating when cured,
    frame assembly.
  8. 　請求項６または７のいずれかに記載のフレーム組立体であって、
    　前記接着剤は、繊維を混ぜたものである、
    　フレーム組立体。     A frame assembly according to any of claims 6 or 7,
    The adhesive is a mixture of fibers,
    frame assembly.
  9. 　請求項１ないし８に記載のフレーム組立体であって、
    　２つの前記開口部の少なくとも一方は、内部に搭載パーツを備える、
    　フレーム組立体。     A frame assembly according to any one of claims 1 to 8,
    at least one of the two openings comprises a mounting part inside;
    frame assembly.
  10. 　請求項９に記載のフレーム組立体であって、
    　前記搭載パーツは、バッテリーケースである、
    　フレーム組立体。     A frame assembly according to claim 9, comprising:
    The mounting part is a battery case,
    frame assembly.
  11. 　請求項９または１０に記載のフレーム組立体であって、
    　前記搭載パーツは、２つの前記固定部材の一方に固定され、２つの前記開口部内に跨って備えられる、
    　フレーム組立体。     A frame assembly according to claim 9 or 10,
    The mounting part is fixed to one of the two fixing members and provided across the two openings,
    frame assembly.
  12. 　請求項９または１０に記載のフレーム組立体であって、
    　前記搭載パーツは、２つの前記固定部材の間であって、下側の固定部材に固定され、前記下側の固定部材の開口部内に備えられる、
    　フレーム組立体。     A frame assembly according to claim 9 or 10,
    The mounting part is fixed to the lower fixing member between the two fixing members and is provided in the opening of the lower fixing member.
    frame assembly.
  13. 　請求項１１または１２に記載のフレーム組立体であって、
    　前記搭載パーツは、前記第１のフレーム部材と、前記第２のフレーム部材とからなる面および該面を直交する軸により規定される方向に対して傾斜して設けられる、
    　フレーム組立体。     A frame assembly according to claim 11 or 12, comprising
    The mounting part is inclined with respect to a direction defined by a plane formed by the first frame member and the second frame member and an axis perpendicular to the plane.
    frame assembly.
  14. 　飛行体用のフレーム組立体の製造方法であって、
    　少なくとも２つの並行し第１の方向に延在する第１のフレーム部材と、前記第１の方向に垂直な第２の方向に延在する第２のフレーム部材のそれぞれに固定部材を固定する、
    　フレーム組立体の製造方法。

          A method of manufacturing a frame assembly for an aircraft, comprising:
    securing a securing member to each of at least two parallel first frame members extending in a first direction and second frame members extending in a second direction perpendicular to the first direction;
    A method of manufacturing a frame assembly.
PCT/JP2022/011413 2021-04-23 2022-03-14 Frame assembly and method for manufacturing same WO2022224630A1 (en)

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CN202210429963.8A CN115230935A (en) 2021-04-23 2022-04-22 Frame assembly and method for manufacturing frame assembly
CN202220945518.2U CN219154730U (en) 2021-04-23 2022-04-22 Frame assembly

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140145026A1 (en) * 2012-11-28 2014-05-29 Hans Skjersaa Unmanned Aerial Device
JP2017193208A (en) * 2016-04-18 2017-10-26 株式会社自律制御システム研究所 Small-sized unmanned aircraft
US20180118322A1 (en) * 2016-04-06 2018-05-03 Benjamin Harris Folding heavy-lift unmanned vehicle frame

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140145026A1 (en) * 2012-11-28 2014-05-29 Hans Skjersaa Unmanned Aerial Device
US20180118322A1 (en) * 2016-04-06 2018-05-03 Benjamin Harris Folding heavy-lift unmanned vehicle frame
JP2017193208A (en) * 2016-04-18 2017-10-26 株式会社自律制御システム研究所 Small-sized unmanned aircraft

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