Outer 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 outer power arm structure and system arrangement of a composite wing electric aircraft, which comprises an outer power arm, system equipment is arranged on one side of the outer power arm, and a fairing is arranged at the top of the outer power arm. The combined type composite wing has the advantages of being convenient to disassemble and assemble, the frame type outer power arm and effective in cooling, an innovative suspension type structure is adopted, the outer power arm is connected with the wing, the disassembly and assembly process of the outer power arm is facilitated, the maintenance efficiency is improved, the overall manufacturing difficulty and assembly complexity of the combined type composite wing are effectively reduced, and the combined type composite wing is suitable for popularization and application. The outer power arm is of a frame type structure, the structure is simple and clear, the manufacturing difficulty of the outer power arm is greatly reduced, and the production process is more efficient; in order to further improve the performance, a circulating water cooling system is adopted in the outer power arm, heat generated in the working process of the motor can be effectively dissipated, and it is ensured that the motor is always kept within a proper working temperature range.

Description

TECHNICAL FIELD

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

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

[0003] The current composite wing airplane outer power arm design is quite innovative, which adopts a fusion structure. This structure ingeniously divides the outer power arm into three parts. The middle part is seamlessly integrated with the wing. This design not only enhances the structural strength of the wing, but also optimizes the aerodynamic performance. The remaining two parts of the outer power arm are assembled at the front and rear positions of the wing. This layout ensures stable power output and control performance during flight.

[0004] However, this fusion structure design also brings certain challenges. On the one hand, it increases the difficulty of manufacturing the wing, as the wing and the middle part of the outer power arm need to be precisely integrated to ensure the stability and reliability of the overall structure. On the other hand, this design also increases the procedures and workload for assembly. The assembly personnel need to accurately position and install the front and rear parts of the outer power arm to ensure their perfect fit with the integrated part of the wing. SUMMARY

[0005] The utility model aims at providing a kind of composite wing electric airplane's outer power arm structure and system arrangement, with the advantages of convenient disassembly and assembly, frame outer power arm and effective cooling, solve the problem 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 outer power arm structure and system arrangement, including outer power arm, the side of the outer power arm is provided with system equipment, the top of the outer power arm is provided with fairing.

[0007] The outer power arm comprises a skin, an inner cavity of the skin is provided with a frame assembly, the frame assembly comprises two composite material frame sixes located at the outermost sides, opposite sides of the two composite material frame sixes are provided with composite material frame fives, opposite sides of the two composite material frame fives are provided with composite material frame fours, opposite sides of the two composite material frame fours are provided with composite material frame threes, opposite sides of the two composite material frame threes are provided with composite material frame twos, opposite sides of the two composite material frame twos are provided with three composite material frame ones, opposite sides of the composite material frame one and the composite material frame two are fixedly connected with two joints, the joint and the frame assembly are connected through the mode of glue jointing and screwing at the same time, the joint and the skin are connected through the mode of glue jointing and screwing at the same time, both sides of the skin are fixedly connected with sand-proof covers, one side of the sand-proof cover is fixedly connected with the frame assembly, opposite sides of the composite material frame five and the composite material frame six are fixedly connected with supports.

[0008] The system device comprises a motor which is bolted to one side of the support, a heat exchanger which is arranged between the composite material frame three, the composite material frame four and the composite material frame five, a motor control unit which is arranged between the composite material frame two and the composite material frame three, a cooling water pump which is arranged between the composite material frame two and the composite material frame two located at the left side, and a cooling water kettle which is arranged between the composite material frame one located at the right side and the composite material frame two.

[0009] Further, as a preferred embodiment of the utility model, the two sides of the top and the bottom of the skin are provided with cooling grilles.

[0010] Further, as a preferred embodiment of the utility model, the two sides of the front side and the back side of the skin are provided with maintenance access covers, and the number of the maintenance access covers is four.

[0011] Further, as a preferred embodiment of the utility model, one side of the joint is provided with a reinforcing piece.

[0012] Further, as a preferred embodiment of the utility model, opposite sides of the two composite material frame ones located at the left side and opposite sides of the composite material frame one and the composite material frame three located at the right side are fixedly connected with device supports, and one side of the cooling water kettle and the cooling water pump is fixedly connected with the device support.

[0013] Beneficial effects, the technical scheme of the application has the following technical effects: the utility model has the advantages of convenient disassembly and assembly, frame type outer power arm and effective cooling.

[0014] The innovative suspension structure connects the external power arm and the wing, facilitates the disassembly and assembly process of the external power arm, improves the maintenance efficiency, and effectively reduces the overall manufacturing difficulty and assembly complexity of the blended wing.

[0015] In order to further improve the performance, the circulating water cooling system is adopted inside the external power arm, which can effectively dissipate the heat generated by the motor during operation, ensure that the motor always maintains in the appropriate working temperature range, thereby prolonging the service life and improving the reliability.

[0016] In addition, the external power arm is also designed with cooling grilles, which cooperate with the cooling air flow channels formed inside to form a composite cooling system. This system and the water cooling method complement each other and jointly act on the electrical equipment, further reducing the working temperature and ensuring the stability and safety of the equipment under long-time high-intensity operation.

[0017] It should be understood that all combinations of the foregoing concepts and additional concepts described in greater detail below can be seen as part of the utility model subject matter of the present disclosure, as long as such concepts do not contradict each other. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings are included to provide a further understanding of the present utility model, and constitute a part of the specification, which together with the embodiments of the present utility model, serve to explain the present utility model, and do not constitute a limitation on the present utility model. In the drawings:

[0019] Figure 1 It is a structural schematic diagram of the present utility model;

[0020] Figure 2 It is a partial split state perspective schematic diagram of the external power arm and system equipment of the present utility model;

[0021] Figure 3 It is a frame assembly perspective structural schematic diagram of the present utility model.

[0022] In the drawings, the meanings of various reference signs are as follows: 1, external power arm; 101, skin; 102, frame assembly; 1021, composite material frame one; 1022, composite material frame two; 1023, composite material frame three; 1024, composite material frame four; 1025, composite material frame five; 1026, composite material frame six; 103, joint; 1031, reinforcing piece; 104, sandproof cover; 105, cooling grille; 106, support; 107, maintenance access cover; 108, equipment support; 2, system equipment; 201, motor; 202, heat exchanger; 203, motor control unit; 204, cooling water pump; 205, cooling water kettle; 3, fairing. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. To better understand the technical content of the present utility model, specific embodiments are provided and described in conjunction with the accompanying drawings. Various aspects of the present utility model are described in this disclosure with reference to the accompanying drawings, which show many illustrative embodiments. It should be understood that the various concepts and embodiments described above, as well as those described in more detail below, can be implemented in any of many ways. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0024] Compound-wing electric aircraft have internal and external power arms; this application only discusses the external power arm.

[0025] As attached Figure 1 To be continued Figure 3 As shown: This embodiment provides an external power arm structure and system layout for a compound wing electric aircraft, including an external power arm 1, a system device 2 disposed on one side of the external power arm 1, and a fairing 3 disposed on the top of the external power arm 1.

[0026] The external power boom 1 includes a skin 101, and a frame assembly 102 is provided inside the skin 101. The skin 101 and the frame assembly 102 are connected by adhesive bonding and riveting. The frame assembly 102 includes two outermost composite material frames 1026. On the opposite side of each of the two composite material frames 1026, a composite material frame 1025 is provided. On the opposite side of each of the two composite material frames 1025, a composite material frame 1024 is provided. On the opposite side of each of the two composite material frames 1024, a composite material frame 1023 is provided. On the opposite side of each of the two composite material frames 1023, a composite material frame 1022 is provided. Three composite material frames 1021 are provided on one side opposite to the two composite material frames 2 1022. Two joints 103 are fixedly connected to the opposite side of composite material frames 1021 and composite material frames 2 1022. The joints 103 are connected to the frame assembly 102 by both adhesive bonding and screwing. The joints 103 are connected to the skin 101 by both adhesive bonding and screwing. Sandproof covers 104 are fixedly connected to both sides of the skin 101. One side of the sandproof cover 104 is fixedly connected to the frame assembly 102. Supports 106 are fixedly connected to the opposite side of composite material frames 5 1025 and composite material frames 6 1026.

[0027] The system device 2 comprises a motor 201 bolted to one side of the support 106, a heat exchanger 202 arranged between the composite material frame three 1023, the composite material frame four 1024 and the composite material frame five 1025, a motor control unit 203 arranged between the composite material frame two 1022 and the composite material frame three 1023, the motor control unit 203 being a prior art, the working principle of which is well known to those skilled in the art, a cooling water pump 204 arranged between the composite material frame two 1022 and the composite material frame two 1022 on the left side, and a cooling water kettle 205 arranged between the composite material frame one 1021 on the right side and the composite material frame two 1022.

[0028] Specifically, the top and bottom of the skin 101 are provided with cooling grilles 105 on both sides.

[0029] In this embodiment: through the setting of the cooling grilles 105, an additional cooling airflow passage is provided to assist the motor 201, the heat exchanger 202 and the motor control unit 203 in heat exchange.

[0030] Specifically, the front and rear sides of the skin 101 are provided with maintenance access covers 107 on both sides, and the number of the maintenance access covers 107 is four.

[0031] In this embodiment: through the setting of the maintenance access covers 107, the installation, disassembly and maintenance of the device are facilitated.

[0032] Specifically, one side of the joint 103 is provided with a reinforcing member 1031.

[0033] In this embodiment: through the setting of the reinforcing member 1031, the stability of the structure between the frame assembly 102 and the joint 103 is strengthened, and the use strength of the joint 103 is improved.

[0034] Specifically, the opposite side of the two composite material frames one 1021 on the left side and the opposite side of the composite material frame one 1021 on the right side and the composite material frame three 1023 are fixedly connected with a device support 108, and one side of the cooling water kettle 205 and the cooling water pump 204 is fixedly connected with the device support 108.

[0035] In this embodiment: through the setting of the device support 108, the connection strength between the cooling water kettle 205, the cooling water pump 204 and the frame assembly 102 is strengthened, and the stability of the cooling water kettle 205 and the cooling water pump 204 is improved.

[0036] The working principle and use process of the utility model: frame assembly 102 as the core framework of outer power arm 1, through the way of cementing and riveting and skin 101 closely connected, for outer power arm 1 bear the load of torsion resistance, and through skin 101 provides aerodynamic shape and provides bending load capacity, on the opposite side of composite material frame six 1026 and composite material frame five 1025 installs support 106, for installing motor 201, and the lift load generated by motor 201 is transferred to outer power arm 1, in order to guarantee the power requirement of the take-off of the aircraft, the support 106 keeps the included angle of 5 ° with the ground when installing, ensure the effective transmission of power and the stable take-off of the aircraft, joint 103 as the connecting bridge of frame assembly 102 and skin 101 and other components, adopts the double connection mode of cementing and screwing, ensure the firmness and reliability of connection, in order to reduce the influence of bolt of frame assembly 102 and joint 103 connecting place on structure, especially increase the reinforcing member 1031 at the connecting place, further improve the strength and stability of structure, then utilize joint 103 and wing connection, the load of outer power arm 1 can be smoothly transferred to wing, provide necessary lift support for the aircraft, in order to ensure the continuous and efficient operation of motor 201, set up heat exchanger 202 to cool it, the water in cooling kettle 205 is circulated into heat exchanger 202, provides the continuous cooling effect for motor 201 by the way of heat exchange, and under the action of motor control unit 203, control the operation of motor 201, in order to facilitate the installation, disassembly and maintenance of electrical equipment, set up maintenance access cover 107 on the left and right of the front side and the rear side of outer power arm 1, not only improve the convenience of maintenance, further, the addition of sandproof cover 104 and cooling grille 105 provides additional cooling airflow passage for outer power arm 1, auxiliary motor 201 and motor control unit 203 and motor control unit 203 carry out heat exchange, for reducing the working temperature of electrical equipment, ensure its long-term stable operation.

[0037] It should be noted that, in this text, relational terms such as first and second and the like are used merely to distinguish one entity or action from another, without necessarily requiring or implying that there is any such actual relationship or order between such entities or actions.

[0038] Although the utility model has disclosed as above with preferred embodiment, 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 defined by the claims.

Claims

1. An external power arm structure and system arrangement for a compound wing electric aircraft, comprising an external power arm (1), characterized in that: A system device (2) is provided on one side of the external power arm (1), and a fairing (3) is provided on the top of the external power arm (1); The external power arm (1) includes a skin (101), and a frame assembly (102) is provided in the inner cavity of the skin (101). The frame assembly (102) includes two outermost composite material frames six (1026), and a composite material frame five (1025) is provided on the opposite side of each of the two composite material frames six (1026). A composite material frame four (1024) is provided on the opposite side of each of the two composite material frames five (1025), a composite material frame three (1023) is provided on the opposite side of each of the two composite material frames four (1024), a composite material frame two (1022) is provided on the opposite side of each of the two composite material frames three (1023), and three composite material frames are provided on the opposite side of each of the two composite material frames two (1022). Material frame one (1021), two joints (103) are fixedly connected to the opposite side of the composite material frame one (1021) and composite material frame two (1022). The joints (103) are connected to the frame assembly (102) by both adhesive bonding and screwing. The joints (103) are connected to the skin (101) by both adhesive bonding and screwing. The surface of the joints (103) is fixedly connected to the skin (101). Sandproof covers (104) are fixedly connected to both sides of the skin (101). One side of the sandproof cover (104) is fixedly connected to the frame assembly (102). Supports (106) are fixedly connected to the opposite side of the composite material frame five (1025) and composite material frame six (1026). The system equipment (2) includes a motor (201) bolted to one side of the support (106), a heat exchanger (202) is provided between the composite material frame three (1023), composite material frame four (1024) and composite material frame five (1025), a motor control unit (203) is provided between the composite material frame two (1022) and composite material frame three (1023), a cooling water pump (204) is provided between the composite material frame two (1022) and the composite material frame two (1022) located on the left, and a cooling water tank (205) is provided between the composite material frame one (1021) and composite material frame two (1022) located on the right.

2. The external power arm structure and system arrangement of a compound wing electric aircraft according to claim 1, characterized in that: Cooling grilles (105) are provided on both sides of the top and bottom of the skin (101).

3. The external power arm structure and system layout of a compound wing electric aircraft according to claim 1, characterized in that: The skin (101) is provided with maintenance cover (107) on both the front and rear sides, and the number of maintenance cover (107) is four.

4. The external power arm structure and system arrangement of a compound wing electric aircraft according to claim 1, characterized in that: A reinforcing member (1031) is provided on one side of the connector (103).

5. The external power arm structure and system arrangement of a compound wing electric aircraft according to claim 1, characterized in that: Equipment brackets (108) are fixedly connected to the opposite sides of the two composite material frames (1021) on the left and the opposite sides of the composite material frames (1021) and (1023) on the right. The cooling water tank (205) and the cooling water pump (204) are fixedly connected to the equipment brackets (108) on one side.

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