Inner power arm structure and system arrangement of composite wing electric aircraft

Abstract

The utility model relates to the technical field of electric aircrafts, in particular to an inner power arm structure and system arrangement of a composite wing electric aircraft, which is characterized by comprising an inner power arm, system equipment is arranged in the inner power arm, and a fairing is arranged at the top of the inner power arm; the inner power arm comprises a skin located on the outer side, and a frame structure is arranged in an inner cavity of the skin. The frame structure sequentially comprises a first bearing frame, a second bearing frame, a third bearing frame, a fourth bearing frame, a fifth bearing frame, a sixth bearing frame, a seventh bearing frame, an eighth bearing frame, a ninth bearing frame, a tenth bearing frame, an eleventh bearing frame, a twelfth bearing frame, a thirteenth bearing frame, a fourteenth bearing frame, a fifteenth bearing frame and a sixteenth bearing frame from left to right. The frame type power arm has the advantages of being convenient and fast to disassemble and assemble, an innovative suspension type structure is adopted, the power arm is connected with the wings, the disassembly and assembly process of the power arm is facilitated, the power arm adopts the frame type structure, and the manufacturing difficulty of the power arm is greatly reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to electric airplane technical field, concretely is a kind of composite wing electric airplane's inner power arm structure and system arrangement. BACKGROUND

[0002] Electric airplane refers to the airplane driven by motor instead of internal combustion engine, and the power source includes fuel cell, solar cell, super capacitor, wireless energy transmission or other kinds of battery etc.

[0003] The power arm of current composite wing airplane adopts fusion structure, that is, the power arm is divided into three parts, the middle part is integrated with wing, and the other two parts are assembled in front and back of wing, such design method; manufacturing dimension upgrades, wing needs to complete co-curing forming of composite material main structure and power arm middle section synchronously, and higher requirements are proposed to material compatibility and forming temperature field control.

[0004] Therefore, there is an urgent need for a kind of composite wing electric airplane's inner power arm structure and system arrangement to solve the above problems. INVENTION CONTENTS

[0005] The utility model aims at providing a kind of composite wing electric airplane's inner power arm structure and system arrangement, with the advantages of convenient disassembly and assembly, frame power arm, solve the problems proposed in the above background technology.

[0006] To achieve the above purpose, the utility model provides the following technical scheme: a kind of composite wing electric airplane's inner power arm structure and system arrangement including inner power arm, the inside of the inner power arm is provided with system equipment, the top of the inner power arm is provided with fairing.

[0007] The inner power arm includes skin located at the outer side, the inner cavity of the skin is provided with frame structure, the frame structure sequentially includes bearing frame one, bearing frame two, bearing frame three, bearing frame four, bearing frame five, bearing frame six, bearing frame seven, bearing frame eight, bearing frame nine, bearing frame ten, bearing frame eleven, bearing frame twelve, bearing frame thirteen, bearing frame fourteen, bearing frame fifteen and bearing frame sixteen from left to right.

[0008] The opposite side of the bearing frame six and the bearing frame seven is fixedly connected with two joints, the joint is connected with the frame structure by means of gluing and screwing, the joint is connected with the skin by means of gluing and screwing, one side of the bearing frame one and the bearing frame sixteen is fixedly connected with a sandproof cover, the inner cavities of the bearing frame one, the bearing frame two, the bearing frame three and the bearing frame four are provided with a battery bracket, the opposite side of the bearing frame one and the bearing frame two and the opposite side of the bearing frame fifteen and the bearing frame sixteen are fixedly connected with a support, the inner cavities of the bearing frame eleven, the bearing frame twelve, the bearing frame thirteen and the bearing frame fourteen are fixedly connected with an equipment support.

[0009] The system equipment comprises a motor connected to one side of the support, the top of the battery bracket is provided with a battery, the opposite side of the bearing frame eleven and the bearing frame twelve and the opposite side of the bearing frame thirteen and the bearing frame fourteen are provided with two motor control units, the bearing frame ten and the bearing frame eleven are provided with a cooling fan, and the bearing frame seven and the bearing frame eight are provided with a battery energy distribution unit.

[0010] Further, as a preferred embodiment of the utility model, the battery bracket comprises a bottom plate, the two sides of the top of the bottom plate are fixedly connected with rail edges, the top of the bottom plate is provided with a battery plate, one side of the battery plate is connected with the frame structure by means of bolting, and the battery is located on the top of the battery plate.

[0011] Further, as a preferred embodiment of the utility model, the two sides of the top of the battery plate are fixedly connected with two lifting rings.

[0012] Further, as a preferred embodiment of the utility model, the one side of the rail edge is embedded with a plurality of track balls.

[0013] Further, as a preferred embodiment of the utility model, the surface of the skin is provided with four maintenance access covers, the two maintenance access covers on the left side are symmetrically arranged, and the two maintenance access covers on the right side are arranged in a staggered manner.

[0014] The technical scheme has the following beneficial effects: the utility model has the advantages of convenient disassembly and assembly and frame power arm.

[0015] The innovative suspension structure connects the power arm with the wing, facilitating the disassembly and assembly process of the power arm, and the power arm itself adopts a frame structure, so that the manufacturing difficulty is greatly reduced.

[0016] In order to further improve the performance, the cooling airflow passage is additionally provided on the sandproof cover and the cooling fan, and the motor and the motor control unit are assisted to exchange heat.

[0017] Finally, the connection mode of the suspension type power arm-wing is used; the mounting mode and mounting structure of the battery are provided, and the mounting and dismounting of the battery are facilitated.

[0018] It should be appreciated that all combinations of the aforementioned concepts and additional concepts described in greater detail below can be viewed as being part of a single inventive subject matter, unless such concepts are incompatible with each other as specified by the claims. BRIEF DESCRIPTION OF DRAWINGS

[0019] The accompanying drawings are included to provide a further understanding of the present application and are incorporated in and constitute a part of this specification, illustrate embodiments of the present application and are used to explain the present application, and do not constitute a limitation of the present application. In the drawings:

[0020] Figure 1 It is a schematic diagram of the structure of the present application;

[0021] Figure 2 It is a schematic diagram of the partial split state of the inner power arm and system equipment of the present application;

[0022] Figure 3 It is a schematic diagram of the frame structure of the present application;

[0023] Figure 4 It is a schematic diagram of the battery bracket of the present application;

[0024] Figure 5 It is a schematic diagram of the split state of the battery bracket of the present application.

[0025] In the drawings, the meanings of the reference signs are as follows: 1, inner power arm; 11, skin; 12, frame structure; 121, bearing frame one; 122, bearing frame two; 123, bearing frame three; 124, bearing frame four; 125, bearing frame five; 126, bearing frame six; 127, bearing frame seven; 128, bearing frame eight; 129, bearing frame nine; 1210, bearing frame ten; 1211, bearing frame eleven; 1212, bearing frame twelve; 1213, bearing frame thirteen; 1214, bearing frame fourteen; 1215, bearing frame fifteen; 1216, bearing frame sixteen; 13, joint; 14, sandproof cover; 15, battery bracket; 151, bottom plate; 152, rail edge; 153, battery plate; 154, rail ball; 155, lifting ring; 16, support; 17, maintenance access cover; 18, equipment support; 2, system equipment; 21, motor; 22, battery; 23, motor control unit; 24, cooling fan; 25, battery energy distribution unit; 3, fairing. DETAILED DESCRIPTION

[0026] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. In order to understand the technical contents of the present application more clearly, specific embodiments are described below and the accompanying drawings are described as follows. The aspects of the present application are described in the present disclosure with reference to the drawings, and many embodiments are shown in the drawings. It should be understood that the various concepts and embodiments introduced above, and those concepts and embodiments described in more detail below can be implemented in any one of many ways. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of the present application.

[0027] The composite wing electric aircraft has inner and outer power arms, and the present application only discusses the inner power arm.

[0028] As shown in the accompanying Figure 1 to the accompanying Figure 5 It is shown that the embodiment provides an inner power arm structure and system arrangement of a composite wing electric aircraft, which comprises an inner power arm 1, a system device 2 arranged inside the inner power arm 1, and a fairing 3 arranged at the top of the inner power arm 1.

[0029] The inner power arm 1 comprises a skin 11 located on the outer side, and the inner cavity of the skin 11 is provided with a frame structure 12, which comprises, in sequence from left to right, a bearing frame one 121, a bearing frame two 122, a bearing frame three 123, a bearing frame four 124, a bearing frame five 125, a bearing frame six 126, a bearing frame seven 127, a bearing frame eight 128, a bearing frame nine 129, a bearing frame ten 1210, a bearing frame eleven 1211, a bearing frame twelve 1212, a bearing frame thirteen 1213, a bearing frame fourteen 1214, a bearing frame fifteen 1215, and a bearing frame sixteen 1216.

[0030] The opposite sides of the bearing frame six 126 and the bearing frame seven 127 are fixedly connected with two joints 13, the joints 13 are connected with the frame structure 12 by means of gluing and screwing, the joints 13 are connected with the skin 11 by means of gluing and screwing, one side of the bearing frame one 121 and the bearing frame sixteen 1216 is fixedly connected with a sandproof cover 14, the inner cavities of the bearing frame one 121, the bearing frame two 122, the bearing frame three 123, and the bearing frame four 124 are provided with a battery bracket 15, the opposite sides of the bearing frame one 121 and the bearing frame two 122 and the opposite sides of the bearing frame fifteen 1215 and the bearing frame sixteen 1216 are fixedly connected with a support 16, and the inner cavities of the bearing frame eleven 1211, the bearing frame twelve 1212, the bearing frame thirteen 1213, and the bearing frame fourteen 1214 are fixedly connected with a device support 18.

[0031] The system device 2 comprises a motor 21 bolted to one side of the support 16, a battery 22 arranged on the top of the battery bracket 15, two motor control units 23 arranged on opposite sides of the bearing frame eleven 1211 and the bearing frame twelve 1212, and the bearing frame thirteen 1213 and the bearing frame fourteen 1214, a cooling fan 24 arranged between the bearing frame ten 1210 and the bearing frame eleven 1211, and a battery energy distribution unit 25 arranged between the bearing frame seven 127 and the bearing frame eight 128. The motor control unit 23 and the battery energy distribution unit 25 belong to the prior art, and their working principles are well known to those skilled in the art.

[0032] Specifically, the battery bracket 15 comprises a bottom plate 151, two rail edges 152 fixedly connected to the top of the bottom plate 151, and a battery plate 153 arranged on the top of the bottom plate 151. The battery plate 153 is bolted to the frame structure 12 on one side, and the battery 22 is located on the top of the battery plate 153.

[0033] In this embodiment, the bottom plate structure of the battery bracket 15 is formed by the cooperation of the bottom plate 151, the rail edge 152, and the battery plate 153. The battery bracket 15 is fixedly connected to the battery 22 by bolting, and the rail edge 152 serves as a support and guide for the battery 22.

[0034] Specifically, the top of the battery plate 153 is fixedly connected to two lifting rings 155 on both sides.

[0035] In this embodiment, the lifting ring 155 is provided to facilitate the lifting and use of the battery 22, reducing the risk of manual handling.

[0036] Specifically, the rail edge 152 is embedded with a plurality of track balls 154 on one side.

[0037] In this embodiment, the track ball 154 is provided to serve as a guide and reduce friction, facilitating the installation and removal of the battery 22.

[0038] Specifically, the surface of the skin 11 is provided with four maintenance access covers 17. The left two maintenance access covers 17 are arranged symmetrically, and the right two maintenance access covers 17 are arranged in a staggered manner.

[0039] In this embodiment, the maintenance access cover 17 is provided, wherein the left two maintenance access covers 17 are symmetrically designed to facilitate the installation and maintenance of the battery 22, and the right two maintenance access covers 17 are designed in a staggered manner to facilitate the maintenance and installation of the motor control units 23 in front and back.

[0040] Working principle: the frame structure 12 is glued and riveted with the skin 11 to form the skeleton of the skin 11, which bears the anti-torsion load for the inner power arm 1, and provides the aerodynamic shape and the bending load capacity through the skin 11, then the support 16 is used to install the motor 21, which drives the propeller to rotate to provide lift, the load is transmitted from the propeller to the support 16, and then to the inner power arm 1, finally the aircraft is vertically pulled up, in order to ensure the power demand of the aircraft during take-off, the support 16 is installed with a 5° angle with the ground, the joint 13 and the frame structure 12 are connected by gluing and screwing, and are connected with the skin 11 together, in order to ensure the influence of the bolts on the structure at the connection between the frame structure 12 and the joint 13, metal reinforcing parts can be added at the connection, further, the battery 22 provides power for the aircraft, the motor 21 provides energy for the system, and the cooling fan 24 introduces cold air into the inner power arm 1 to provide continuous heat dissipation for the motor 21, the battery 22 and the motor control unit 23; in addition, the motor control unit 23 is set to control the operation of the battery 22, in order to facilitate the installation, disassembly and maintenance of electrical equipment, two maintenance covers 17 are arranged on the left and right sides of the inner power arm 1, the left two maintenance covers 17 are designed in symmetry, which facilitates the installation and maintenance of the battery 22; the right two maintenance covers 17 are designed in staggered manner, which facilitates the maintenance and installation of the front and rear motor control units 23; and the sandproof cover 14 and the cooling fan 24 additionally provide a cooling air passage to assist the motor 21 and the motor control unit 23 in heat exchange; finally, the battery bracket 15 mainly provides a fixed position for the battery 22 in the inner power arm 1, and its design facilitates the installation and disassembly of the battery, the track ball 154 is installed on the track edge 152 by bolts, and then connected with the bottom plate 151 by bolts to form the bottom plate structure of the battery bracket 15, the battery bracket 15 and the battery 22 are connected and fixed by bolts, wherein the track edge 152 plays a supporting and guiding role for the battery 22, the track ball 154 plays a guiding and friction reducing role, which facilitates the installation and disassembly of the battery 22, when the battery 22 needs to be installed: the battery 22 is first fixed on the battery plate 153, then lifted by the lifting ring 155, and then installed in the inner power arm 1, and then the battery plate 153, the battery 22 and the bottom plate 151 are fixed in the inner power arm 1 by bolts through the opening space of the maintenance cover 17 and the bearing frame one 121; when the battery 22 needs to be unloaded: through the opening space of the maintenance cover 17 and the bearing frame one 121, the bolts are disassembled, the battery 22 and the battery plate 153 (which are integrated at this time) are slid along the track edge 152, and finally the battery 22 and the battery plate 153 are unloaded together through the lifting ring 155, considering that the weight of the battery 22 is very large, lifting rings 155 are additionally arranged in front of and behind the battery plate 153 to facilitate lifting and reduce the risk of personnel carrying.

[0041] It is to be noted that the relational terms herein, such as first and second, and the like, are used solely to distinguish one from another entity or action without necessarily requiring or implying any such actual relationship or order between such entities or actions.

[0042] Although the utility model has disclosed as above with preferred embodiments, it is not used to limit the utility model. Those skilled in the art to which the utility model belongs can make various changes and decorations without departing from the spirit and scope of the utility model. Therefore, the protection scope of the utility model shall be subject to the definition of the claims.

Claims

1. An internal power arm structure and system layout for a compound-wing electric aircraft, characterized in that: It includes an inner power arm (1), the inner power arm (1) is equipped with system equipment (2), and the top of the inner power arm (1) is equipped with a fairing (3); The inner power arm (1) includes a skin (11) located on the outer side. The inner cavity of the skin (11) is provided with a frame structure (12). The frame structure (12) includes, from left to right, a first load-bearing frame (121), a second load-bearing frame (122), a third load-bearing frame (123), a fourth load-bearing frame (124), a fifth load-bearing frame (125), a sixth load-bearing frame (126), a seventh load-bearing frame (127), a eighth load-bearing frame (128), a ninth load-bearing frame (129), a tenth load-bearing frame (1210), an eleventh load-bearing frame (1211), a twelfth load-bearing frame (1212), a thirteenth load-bearing frame (1213), a fourteenth load-bearing frame (1214), a fifteenth load-bearing frame (1215), and a sixteenth load-bearing frame (1216). The six (126) and seven (127) bearing frames are fixedly connected to two joints (13) on opposite sides. The joints (13) are connected to the frame structure (12) by both adhesive bonding and screwing. The joints (13) are also connected to the skin (11) by both adhesive bonding and screwing. One side of the first (121) and sixteen (1216) bearing frames is fixedly connected to a sandproof cover (14). The first (121), second (122), and third (127) bearing frames are fixedly connected to the frame structure (12). The inner cavities of the three (123) and four (124) are provided with a battery bracket (15). The opposite sides of the first (121) and second (122) and the opposite sides of the fifteen (1215) and sixteen (1216) are all fixedly connected with supports (16). The inner cavities of the eleventh (1211), twelfth (1212), thirteenth (1213) and fourteenth (1214) are all fixedly connected with equipment brackets (18). The system device (2) includes a motor (21) bolted to one side of the support (16), a battery (22) is provided on the top of the battery bracket (15), two motor control units (23) are provided on the opposite side of the support frame eleven (1211) and support frame twelve (1212) and on the opposite side of support frame thirteen (1213) and support frame fourteen (1214), a cooling fan (24) is provided between support frame ten (1210) and support frame eleven (1211), and a battery energy distribution unit (25) is provided between support frame seven (127) and support frame eight (128).

2. The internal power arm structure and system layout of a compound wing electric aircraft according to claim 1, characterized in that: The battery bracket (15) includes a base plate (151), and two sides of the top of the base plate (151) are fixedly connected to rail edges (152). A battery plate (153) is provided on the top of the base plate (151), and one side of the battery plate (153) is bolted to the frame structure (12). The battery (22) is located on the top of the battery plate (153).

3. The internal power arm structure and system layout of a compound-wing electric aircraft according to claim 2, characterized in that: Two hanging rings (155) are fixedly connected to both sides of the top of the solar panel (153).

4. The internal power arm structure and system layout of a compound wing electric aircraft according to claim 2, characterized in that: Several track balls (154) are embedded on one side of the track edge (152).

5. The internal power arm structure and system layout of a compound wing electric aircraft according to claim 1, characterized in that: The surface of the skin (11) is provided with four maintenance openings (17), with the two maintenance openings (17) on the left side arranged symmetrically and the two maintenance openings (17) on the right side arranged in a staggered manner.

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