CN213705805U - Electric aircraft battery pack's installation device and electric aircraft - Google Patents
Electric aircraft battery pack's installation device and electric aircraft Download PDFInfo
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- CN213705805U CN213705805U CN202021544548.XU CN202021544548U CN213705805U CN 213705805 U CN213705805 U CN 213705805U CN 202021544548 U CN202021544548 U CN 202021544548U CN 213705805 U CN213705805 U CN 213705805U
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- 238000009434 installation Methods 0.000 title claims abstract description 57
- 230000000712 assembly Effects 0.000 claims description 16
- 238000000429 assembly Methods 0.000 claims description 16
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 6
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 239000002131 composite material Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 238000005728 strengthening Methods 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 229910001008 7075 aluminium alloy Inorganic materials 0.000 description 1
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Battery Mounting, Suspending (AREA)
Abstract
The utility model relates to an installation device and electric aircraft of electric aircraft battery package, fuselage mechanism includes among the installation device: a frame assembly and a support frame assembly; the frame assembly includes: relative first fuselage frame and the second fuselage frame that sets up, the support frame subassembly sets up between first fuselage frame and second fuselage frame, and the support frame subassembly includes relative first fuselage support frame and the second fuselage support frame that sets up, and installation mechanism includes: the device comprises a base frame, an installation frame and a support rod assembly, wherein one end of the base frame is connected with a first machine body support frame, the other end of the base frame is connected with a second machine body support frame, the installation frame is arranged above the base frame, and the support rod assembly is arranged between the base frame and the installation frame; the utility model discloses can reduce the probability that the battery package became invalid, simple structure is light, and occupation space is less, reduces the installation, the maintenance of being convenient for.
Description
Technical Field
The utility model relates to a battery package technical field, in particular to installation device and electric aircraft of electric aircraft battery package.
Background
In recent years, the electric airplane has the characteristics of simple structure, convenience in operation and use, good maintainability, low use cost, good economy and the like, and is widely applied to various fields such as transportation, tourism, emergency rescue and the like. The electric airplane adopts the power battery pack and the motor system to replace the traditional fuel engine, does not generate waste gas and exhaust tail gas pollution during working, has lower noise and vibration level, good riding comfort and is a true environment-friendly airplane. The failure probability of the battery pack is higher than that of the traditional fuel engine, and the electric airplane is easy to cause accidents of airplane damage and death due to the failure of the battery pack, so that the current electric airplane generally adopts two or more battery packs connected in parallel as power, and the failure probability is reduced. How to mount a plurality of battery packs and reduce the structural weight becomes the key point of the battery pack mounting structure.
According to one of the existing specifications, the items of mass that may be harmful to the occupants inside the cabin are subjected to static inertial loads corresponding to the following limit load factors: 3.0 upwards and 18.0 forwards; lateral direction 4.5.
According to another current specification, the support structure must be designed to restrain any mass items in the upper and/or rear part of the crew and passenger cabins, possibly for the sea passengers after release during emergency landing, under any extreme inertial load up to that specified in this section. The quality items accounted for include, but are not limited to: rotor, transmission and engine. These mass items must be constrained by the following extreme inertial load coefficients: 1.5g upwards; 12g forwards; 6g in the lateral direction; 12g downwards; backward 1.5 g.
The battery pack of the electric aircraft replaces the engine of the original traditional fuel aircraft, so the airworthiness clause needs to be met.
At present, in the prior art, the battery pack structure is divided into two types, one type is that an internal battery module is a double layer, and an external battery pack is a whole, but the internal module of the battery pack is not physically isolated, so that the failure probability of the battery pack cannot be reduced, and the safety requirement of an electric airplane cannot be met; another kind fixes two battery packages on the support, has carried out physics isolated to the inside module of battery package, and when a battery package became invalid, another battery package was not influenced, can reduce the probability that the battery package became invalid, but its structure is complicated, and weight is heavier, and occupation space is big, does not satisfy the requirement of aircraft to weight.
The above problems are therefore to be solved by the person skilled in the art.
SUMMERY OF THE UTILITY MODEL
In view of the above problems in the prior art, an object of the present invention is to provide an installation apparatus for an electric aircraft battery pack and an electric aircraft, which can reduce the probability of failure of the battery pack, ensure the flight safety of the electric aircraft, have a simple and light structure, and satisfy the requirement of the aircraft on light weight by keeping the structure light when satisfying the load of airworthiness requirement; the two battery packs are fixed together by utilizing the structural characteristics and the strength performance of the battery packs, so that the labor amount is reduced during the installation and the battery replacement, and the maintainability are better; the structure is compact, the occupied space is small, and larger vacant space can be provided for other equipment; according to the mounting structure characteristics of the battery pack, the structural forms of airplanes around the battery pack are arranged, the structure is simple and efficient, and the requirements of the battery pack on an organism supporting structure when inertial load required by airworthiness are met.
In order to solve the problem, the utility model provides an installation device of electric aircraft battery package, include: a body mechanism and a mounting mechanism;
the fuselage mechanism includes: frame subassembly and support frame subassembly, the frame subassembly includes: the first machine body frame and the second machine body frame are oppositely arranged, the support frame assembly is arranged between the first machine body frame and the second machine body frame and comprises a first machine body support frame and a second machine body support frame, and the first machine body support frame and the second machine body support frame are oppositely arranged;
the mounting mechanism includes: basic frame, installation frame and bracing piece subassembly, basic frame's one end with first fuselage support frame is connected, basic frame's the other end with second fuselage support frame is connected, the installation frame sets up basic frame's top, the setting of bracing piece subassembly is in basic frame with between the installation frame.
Furthermore, the machine body mechanism further comprises two groups of pull rod assemblies, one group of pull rod assemblies are arranged on the first machine body frame, and the other group of pull rod assemblies are arranged on the second machine body frame.
Further, the tie rod assembly includes: the pull rod and the pull rod joint, pull rod one end with install the frame connection, the pull rod other end with the pull rod articulate, the pull rod joint is fixed on the frame subassembly.
Furthermore, the support frame component is of a groove type, and the groove opening of the first machine body support frame and the groove opening of the second machine body support frame are oppositely arranged.
Further, the fuselage mechanism still includes strengthening mechanism, strengthening mechanism sets up in the recess of support frame subassembly.
Further, the fuselage mechanism also comprises a fuselage stringer, wherein the fuselage stringer is arranged on the same side of the first fuselage frame or the same side of the second fuselage frame.
Further, the number of the mounting frames is at least one.
Further, the support rod assemblies are at least four groups, and each group of support rod assemblies is arranged between one edge of the base frame and one edge of the opposite installation frame.
Furthermore, the support rod assembly comprises a straight rod and two inclined rods, and the two inclined rods are respectively arranged on two sides of the straight rod.
The utility model also protects an electric aircraft, including above-mentioned arbitrary installation device and the battery package subassembly of electric aircraft battery package, the battery package subassembly includes two at least battery packages, one the battery package sets up in the middle of the foundation frame, another the battery package sets up in the middle of the installation frame
Because of the technical scheme, the utility model discloses following beneficial effect has:
1) the utility model discloses an installation device of an electric aircraft battery pack and an electric aircraft, which reasonably distributes the installation mechanism, occupies small space, is convenient for utilizing the internal space of the aircraft body, has simple and light structure and reduces the cost of the electric aircraft;
2) the utility model discloses an installation device of an electric aircraft battery pack and an electric aircraft, which can form a reasonable force transmission path through the connection of an installation mechanism, an aircraft body frame and an aircraft body support frame, and meet the stress requirement of the battery pack;
3) the utility model discloses an installation device of an electric aircraft battery pack and an electric aircraft, which are provided with a straight rod and an inclined rod, wherein the straight rod and the inclined rod are lighter in structure weight, so that the load of the electric aircraft can be improved, the electric aircraft can bear more battery packs conveniently, and the cruising ability is improved;
4) utility model discloses an installation device and electric aircraft of electric aircraft battery package has two at least battery packages, and is invalid when one of them, and another still can continue to use, guarantees electric aircraft safety flight.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the description of the embodiment or the prior art will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic structural diagram of a mounting device for a battery pack of an electric aircraft according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a fuselage mechanism provided in an embodiment of the present invention;
fig. 3 is a schematic structural diagram of other components in the fuselage mechanism according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a reinforcing mechanism according to an embodiment of the present invention;
FIG. 5 is a schematic structural diagram of a mounting mechanism according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of a support rod assembly according to an embodiment of the present invention;
wherein, 1-fuselage mechanism, 11-frame assembly, 111-first fuselage frame, 112-second fuselage frame, 12-support frame assembly, 121-first fuselage support frame, 122-second fuselage support frame, 13-pull rod assembly, 131-pull rod, 132-pull rod joint, 14-reinforcing mechanism, 15-fuselage stringer, 2-mounting mechanism, 21-base frame, 22-mounting frame, 23-support rod assembly, 231-straight rod, 232-diagonal rod.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with at least one implementation of the invention is included. In the description of the present invention, it is to be understood that the terms "upper", "lower", "left", "right", "top", "bottom", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. Moreover, the terms "first," "second," and the like are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or otherwise described herein.
Example one
In one embodiment, a mounting device for a battery pack of an electric aircraft is provided, which is shown in fig. 1 to 6, and includes: a body mechanism 1 and an installation mechanism 2;
the body mechanism 1 includes: a frame assembly 11 and a support bracket assembly 12, the frame assembly 11 comprising: a first body frame 111 and a second body frame 112, wherein the first body frame 111 and the second body frame 112 are arranged oppositely, the support frame assembly 12 is arranged between the first body frame 111 and the second body frame 112, the support frame assembly 12 comprises a first body support frame 121 and a second body support frame 122, and the first body support frame 121 and the second body support frame 122 are arranged oppositely;
the mounting mechanism 2 includes: basic frame 21, installation frame 22 and bracing piece subassembly 23, the one end of basic frame 21 with first fuselage support frame 121 is connected, the other end of basic frame 21 with second fuselage support frame 122 is connected, installation frame 22 sets up the top of basic frame 21, bracing piece subassembly 23 sets up basic frame 21 with between the installation frame 22.
Specifically, the frame assembly 11 is C-shaped in cross section, and is a main supporting structure for bearing the lateral and circumferential loads of the electric aircraft, and the frame assembly 11 is used for providing support for the support frame assembly 12, the tie rod assembly 13 and the fuselage stringer 15.
Further, the frame assembly 11 is made of a carbon fiber composite material.
Specifically, the body mechanism 1 further includes two sets of pull rod assemblies 13, one set of the pull rod assemblies 13 is disposed on the first body frame 111, the other set of the pull rod assemblies 13 is disposed on the second body frame 112, and the two sets of the pull rod assemblies 13 are disposed opposite to each other.
Further, the tie rod assembly 13 includes: the frame component 11 comprises a pull rod 131 and a pull rod joint 132, wherein one end of the pull rod 131 is connected with the mounting frame 22, the other end of the pull rod 131 is connected with the pull rod joint 132, and the pull rod joint 132 is fixed on the frame component 11.
Further, one end of the pull rod 131 is connected with the pull rod joint 132 through a bolt and a nut, and a gasket is arranged in a gap where the bolt contacts with the pull rod 131 and the pull rod joint 132; the other end of the pull rod 131 is connected with the mounting frame 22 through a bolt and a nut, and a gasket is arranged at the joint of the pull rod 131 and the bolt, so that the concentrated force of a contact area can be dispersed through the gasket, and the safety of the battery pack can be protected.
Further, the tie bar 131 is a two-force bar and only bears axial load, and the tie bar connector 132 and the battery pack corresponding to the mounting frame 22 bear the forward inertia force of the battery pack system.
Further, the tie rod 131 and the tie rod joint 132 are made of aluminum alloy 7075 aluminum alloy, and the selected heat treatment state is T7351.
Specifically, the support frame assembly 12 is of a groove type, and the groove opening of the first body support frame 121 and the groove opening of the second body support frame 122 are disposed oppositely.
In some embodiments, the fuselage mechanism 1 further comprises a stiffening mechanism 14, the stiffening mechanism 14 being disposed within a recess of the support frame assembly 12; the reinforcing means 14 is glued to the base frame 21 and the mounting frame 22.
Reinforcing mechanism 14 is equipped with the internal thread, reinforcing mechanism 14 pass through the bolt with battery package in the basic frame 21 is connected, when dismantling battery package system, only need dismantle the bolt, reduces and dismantles and installation time, reduces the maintenance cost, state reinforcing mechanism 14 and the junction of bolt and set up the pad, can disperse the concentrated power in contact area through the gasket, protect the safety of battery package.
Further, the reinforcing mechanism 14 is made of high-strength steel.
Further, the base frame 21 and the mounting frame 22 are made of carbon fiber composite materials, provide support for the reinforcing mechanism 14, bear downward and lateral loads and partial forward loads of the battery pack mechanism, and are connected with the fuselage frame assembly 11 at two ends to transmit the loads to the fuselage frame assembly 11; the basic frame 21 is further provided with avoidance holes for avoiding when the bolts and the nuts are connected with a plurality of battery packs.
Specifically, the fuselage airframe structure 1 further includes that the fuselage stringers 15 are disposed on the same side of the first fuselage frame 111 or the same side of the second fuselage frame 112.
Preferably, one end of the rear longitudinal frame 15 is connected to the tie bar joint 132 and two sides of the first body frame 111, and is used for bearing a forward load transmitted by a battery pack mechanism; the other end of the fuselage rear stringer 15 is glued to the first fuselage frame 111 and to the outer skin of the fuselage.
Further, the rear side member 15 is made of a carbon fiber composite material.
In particular, the number of said mounting frames 22 is at least one, preferably said mounting frame 22 is one.
Specifically, the support rod assemblies 23 are at least four sets, and each set of the support rod assemblies 23 is disposed between one side of the base frame 21 and an opposite side of the mounting frame 22.
Further, the support rod assembly 23 includes a straight rod 231 and two diagonal rods 232, and the two diagonal rods 232 are respectively disposed on two sides of the straight rod 231.
Further, the straight bar 231 is a round high-strength steel pipe, the straight bar 231 is provided with internal threads, so that the lower end face of the straight bar 231 abuts against the base frame 21 and the upper end face of the straight bar 231 abuts against the mounting frame 22 through bolt connection, a gasket is arranged at the connection position of the straight bar 231 and the bolts, and is used for dispersing the concentrated force of a contact area and protecting the safety of a battery pack, wherein the straight bar 231 is mainly used for bearing the downward load of the battery pack in the mounting frame 22.
Further, the two diagonal rods 232 are welded by steel pipes with different diameters, the lower end face of each diagonal rod 232 abuts against the base frame 21, the upper end face of each diagonal rod 232 abuts against the installation frame 22, a gasket is arranged at the connection position of the straight rod 231 and the bolt and used for dispersing the concentrated force of a contact area, wherein the diagonal rods 232 are mainly used for bearing the forward and lateral loads of the battery pack in the installation frame 22, and the size of each diagonal rod is within the envelope of the upper and lower battery packs, so that the occupied space is small.
This embodiment still provides an electric aircraft, includes any one of the aforesaid electric aircraft battery package's installation device and battery package subassembly 3, battery package subassembly 3 includes two at least battery packages, one the battery package sets up in the middle of the basic frame 21, another the battery package sets up in the middle of the installation frame 22, wherein, two parallelly connected independent battery packages have been separated in physics, can guarantee the redundancy of power battery package, have improved the security of electric aircraft flight.
Specifically, the installation process of the installation device of the electric aircraft battery pack is as follows:
strengthening mechanism 14 splices through the adhesive on the bracing piece subassembly 23, fixes on the assembly type frame subassembly 11, simultaneously handle bracing piece subassembly 23 fuselage longeron 15 with pull rod joint 132 is fixed on the assembly type frame, support piece subassembly 23 with frame subassembly 11 is spliced together with the adhesive, through bolt, auto-lock nut and gasket frame subassembly 11 pull rod joint 132 links together with fuselage longeron 15, the one end of pull rod 131 with bolt, auto-lock nut and gasket with pull rod joint 132 links together, forms the fuselage structure.
The battery pack to be arranged in the installation frame 22 is fixed on an assembly jig, the inclined rod 232 is installed on the installation point of the battery pack in the installation frame 22 through a bolt, a self-locking nut and a gasket, and the straight rod 231 is installed on the installation point of the battery pack in the upper installation frame 22 through a bolt and a gasket, so that the installation of the battery pack in the installation frame 22 and the installation frame 22 is completed. The battery pack to be arranged in the base frame 21 is fixed on an assembly jig, and the installation is completed by connecting the installation point of the battery pack in the base frame 21 with the base frame 21 by using bolts, self-locking nuts and gaskets.
The installation mechanism 2 which is connected is placed in an area formed by the machine body frame assembly 11 in the machine body structure, the supporting frame assembly 12 and the mounting point of the battery pack in the base frame 21 are connected through bolts and gaskets, and the mounting point of the battery pack in the installation frame 22 and the other end of the pull rod 131 are connected through bolts, self-locking nuts and gaskets.
After the steps are completed, the installation of the battery pack installation device of the whole electric airplane is realized.
The embodiment provides a mounting device for a battery pack of an electric airplane and the electric airplane, which can reduce the failure probability of the battery pack, ensure the flight safety of the electric airplane, have a simple and light structure, keep the structure light in weight when meeting the load of airworthiness requirements, and meet the requirements of the airplane on light weight; the two battery packs are fixed together by utilizing the structural characteristics and the strength performance of the battery packs, so that the labor amount is reduced during the installation and the battery replacement, and the maintainability are better; the structure is compact, the occupied space is small, and larger vacant space can be provided for other equipment; according to the mounting structure characteristics of the battery pack, the structural forms of airplanes around the battery pack are arranged, the structure is simple and efficient, and the requirements of the battery pack on an organism supporting structure when inertial load required by airworthiness are met.
The foregoing description has disclosed fully the embodiments of the present invention. It should be noted that those skilled in the art can make modifications to the embodiments of the present invention without departing from the scope of the claims of the present invention. Accordingly, the scope of the claims of the present invention is not to be limited to the specific embodiments described above.
Claims (10)
1. A mounting device for a battery pack of an electric aircraft, comprising: a machine body mechanism (1) and an installation mechanism (2);
the body mechanism (1) comprises: a frame assembly (11) and a support bracket assembly (12), the frame assembly (11) comprising: the first fuselage frame (111) and the second fuselage frame (112) are arranged oppositely, the support frame assembly (12) is arranged between the first fuselage frame (111) and the second fuselage frame (112), the support frame assembly (12) comprises a first fuselage support frame (121) and a second fuselage support frame (122), and the first fuselage support frame (121) and the second fuselage support frame (122) are arranged oppositely;
the mounting mechanism (2) comprises: basic frame (21), installation frame (22) and bracing piece subassembly (23), the one end of basic frame (21) with first fuselage support frame (121) are connected, the other end of basic frame (21) with second fuselage support frame (122) are connected, installation frame (22) set up the top of basic frame (21), bracing piece subassembly (23) set up basic frame (21) with between installation frame (22).
2. The mounting device for the battery pack of the electric airplane as claimed in claim 1, wherein the fuselage mechanism (1) further comprises two sets of tie rod assemblies (13), one set of tie rod assemblies (13) being disposed on the first fuselage frame (111) and the other set of tie rod assemblies (13) being disposed on the second fuselage frame (112).
3. A mounting arrangement for an electric aircraft battery pack according to claim 2, characterised in that the tie rod assembly (13) comprises: the device comprises a pull rod (131) and a pull rod joint (132), wherein one end of the pull rod (131) is connected with the installation frame (22), the other end of the pull rod (131) is connected with the pull rod joint (132), and the pull rod joint (132) is fixed on the frame component (11).
4. The mounting arrangement for an electric aircraft battery pack as claimed in claim 1, characterised in that the support frame assembly (12) is of a recessed type, the recessed opening of the first fuselage support frame (121) and the recessed opening of the second fuselage support frame (122) being oppositely disposed.
5. The mounting device for the battery pack of the electric aircraft according to claim 4,
the fuselage mechanism (1) further comprises a reinforcing mechanism (14), and the reinforcing mechanism (14) is arranged in a groove of the support frame assembly (12).
6. An electric aircraft battery pack mounting arrangement as claimed in claim 1, characterised in that the fuselage mechanism (1) further comprises fuselage stringers (15), the fuselage stringers (15) being arranged on the same side of the first fuselage frame (111) or of the second fuselage frame (112).
7. Installation arrangement of an electric aircraft battery pack according to claim 1, characterised in that the number of the installation frames (22) is at least one.
8. A mounting arrangement for an electric aircraft battery pack according to claim 1, characterised in that the support bar assemblies (23) are of at least four groups, each group of support bar assemblies (23) being arranged between one side of the base frame (21) and an opposite side of the mounting frame (22).
9. The mounting device for the battery pack of the electric aircraft as claimed in claim 8, wherein the support rod assembly (23) comprises a straight rod (231) and two diagonal rods (232), and the two diagonal rods (232) are respectively arranged at two sides of the straight rod (231).
10. An electric aircraft, characterized in that it comprises a battery pack assembly (3) and a mounting device for a battery pack of an electric aircraft according to any one of claims 1 to 9, said battery pack assembly (3) comprising at least two battery packs, one of said battery packs being arranged in the middle of said base frame (21) and the other battery pack being arranged in the middle of said mounting frame (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021544548.XU CN213705805U (en) | 2020-07-30 | 2020-07-30 | Electric aircraft battery pack's installation device and electric aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021544548.XU CN213705805U (en) | 2020-07-30 | 2020-07-30 | Electric aircraft battery pack's installation device and electric aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN213705805U true CN213705805U (en) | 2021-07-16 |
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| CN202021544548.XU Active CN213705805U (en) | 2020-07-30 | 2020-07-30 | Electric aircraft battery pack's installation device and electric aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113844661A (en) * | 2021-10-19 | 2021-12-28 | 西北工业大学 | Hydrogen storage tank mounting support structure for hydrogen energy aircraft |
-
2020
- 2020-07-30 CN CN202021544548.XU patent/CN213705805U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113844661A (en) * | 2021-10-19 | 2021-12-28 | 西北工业大学 | Hydrogen storage tank mounting support structure for hydrogen energy aircraft |
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