CN211017160U

CN211017160U - Electric aircraft battery packaging system

Info

Publication number: CN211017160U
Application number: CN201921902906.7U
Authority: CN
Inventors: 熊俊; 李洪淼; 严飞; 周义
Original assignee: Cetc Wuhu General Aviation Industry Technology Research Institute Co ltd; Cetc Wuhu Diamond Aircraft Manufacture Co ltd
Current assignee: Cetc Wuhu General Aviation Industry Technology Research Institute Co ltd; Cetc Wuhu Diamond Aircraft Manufacture Co ltd
Priority date: 2019-11-06
Filing date: 2019-11-06
Publication date: 2020-07-14
Anticipated expiration: 2029-11-06

Abstract

The utility model discloses an electric aircraft battery packaging system, including set up in the inside battery installation cabin that just is used for holding the power battery module of wing, set up the fire bottle in battery installation cabin, be connected with the fire bottle and stretch into the inside drainage tube of power battery module and set up on the wing and be used for guiding the air current to the inside air inlet unit of power battery module. The utility model discloses an electric aircraft battery packaging system can carry out the ventilation cooling to the battery to can prevent because battery trouble or conflagration cause the catastrophic consequence of aircraft, promote the safe and reliable degree of aircraft power battery.

Description

Electric aircraft battery packaging system

Technical Field

The utility model belongs to the technical field of electric aircraft, specifically speaking, the utility model relates to an electric aircraft battery packaging system.

Background

The existing 2-4 small-sized general airplane power systems are all of a fuel oil type, and heat energy is converted into mechanical energy to provide power for an airplane through combustion of aviation gasoline or kerosene. The combustion emissions of the traditional fuel-oil type airplane are easy to cause environmental pollution, for example, the combustion emissions of sulfur dioxide can cause acid rain, and nitric oxide can destroy the earth ozone layer.

Along with the improvement of environmental protection consciousness of people, research units begin to use clean electric energy as airplane power energy, replace a traditional airplane wing oil tank with a power battery module, and arrange the power battery module between a front beam and a rear beam of a left wing and a right wing respectively for installation, wherein the power battery module comprises a plurality of batteries. The battery can generate heat in the climbing and cruising phases of the airplane, the battery can be burnt under the fault condition, and the prior art lacks a technical means for solving the problems of heat generation and burning of the battery.

SUMMERY OF THE UTILITY MODEL

The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides an electric aircraft battery packaging system, the purpose is the heat dispersion that improves power battery module.

In order to realize the purpose, the utility model discloses the technical scheme who takes does: electric aircraft battery packaging system is including setting up in inside and being used for holding the battery installation cabin of power battery module of wing, setting up the fire bottle in the battery installation cabin, be connected with the fire bottle and stretch into the inside drainage tube of power battery module and set up on the wing and be used for leading the air current to the inside air inlet unit of power battery module.

The air inlet device comprises an air guide main pipe and an air guide manifold connected with the air guide main pipe, the air guide manifold is provided with a plurality of air guide manifolds, each air guide manifold is respectively inserted between two adjacent front-row battery blocks of the power battery module, and a ventilation air guide port which enables the air guide main pipe to be communicated with the external environment is arranged on the wing.

The electric aircraft battery packaging system further comprises an exhaust device which is arranged on the wing and used for exhausting, the exhaust device comprises a plurality of exhaust manifolds, each exhaust manifold is respectively inserted between two adjacent rear-row battery blocks of the power battery module, and an exhaust outlet which enables the exhaust manifolds to be communicated with the external environment is arranged on the wing.

The ventilation bleed air inlet is positioned in the pressure area of the lower wing surface of the front edge of the right wing, and the air outlet is close to the rear edge of the wing.

Set up a plurality of power battery module in the battery installation cabin, all power battery modules are for arranging in proper order along the length direction of wing, the fire extinguishing bottle is arranged between every two adjacent power battery modules.

Set up first rib and second rib in the battery installation cabin, first rib and second rib all set up a plurality ofly and first rib and second rib are interval arrangement, the fire bottle is located between first rib and the second rib, and the second rib has and lets the through-hole that the drainage tube passed, and the power battery module is located between second rib and another first rib.

The inside front-back beam and the back-back beam of setting up of wing, first rib with the second rib is located between front-back beam and the back-back beam and first rib and second rib are connected with front-back beam and back-back beam, fire extinguishing bottle and power battery module are located between front-back beam and the back-back beam.

The front beam, the rear beam and the drainage tube are parallel in length direction, and the drainage tube is positioned between the front row of battery blocks and the rear row of battery blocks of the power battery module.

The wing comprises a wing lower skin, a wing upper skin connected with the wing lower skin and an upper skin cover plate which is detachably connected with the front beam and the rear beam and is positioned above the battery installation cabin.

The battery installation cabin is characterized in that a heat insulation asbestos layer is arranged on a cabin wall of the battery installation cabin, a stainless steel plate layer is arranged on the heat insulation asbestos layer, and a fireproof paint layer is arranged on the stainless steel plate layer.

The utility model discloses an electric aircraft battery packaging system can carry out the ventilation cooling to the battery to can prevent because battery trouble or conflagration cause the catastrophic consequence of aircraft, promote the safe and reliable degree of aircraft power battery.

Drawings

The description includes the following figures, the contents shown are respectively:

FIG. 1 is a schematic diagram of an electric aircraft power cell arrangement;

FIG. 2 is a schematic structural view of an electric aircraft;

FIG. 3 is a schematic diagram of a right wing power cell layout;

FIG. 4 is a schematic diagram of the arrangement of the right power battery module and the fire extinguishing bottle;

FIG. 5 is a cross-sectional view of an airfoil;

FIG. 6 is a schematic view of a battery installation;

FIG. 7 is a schematic view of the arrangement of the battery installation compartment;

FIG. 8 is a partial view of a battery installation compartment fire wall panel;

labeled as: 1. a three-blade tension propeller; 2. an electric motor; 3. a cockpit front windshield; 4. a left side hatch door; 5. a right side hatch door; 6. a left side wing; 7. a right wing; 8. a left winglet; 9. a right winglet; 10. a left aileron; 11. a left outer flap; 12. a left inner flap; 13. a right outer flap; 14. a right inner flap; 15. a right aileron; 16. low flat tail; 17. an elevator; 18. a vertical tail; 19. a rudder; 20. a power battery module; 21. a fire extinguishing bottle; 22. a front beam; 23. a rear beam; 24. A first rib; 25. a second rib; 26. a drainage tube; 27. a main air-entraining pipe; 28. a bleed air manifold; 29. A ventilation air-bleed port; 30. an outlet manifold; 31. a rear row of battery blocks; 32. a front row of battery blocks; 33. an air outlet; 35. a fire extinguisher mounting bracket; 36. a stagnation valve of the bleed pipe; 37. an air outlet manifold stagnation valve 38, a fire bottle stagnation valve; 39. a battery mounting bracket; 40. a wing lower skin; 41. an upper wing skin; 42. an upper skin cover plate; 43. a hinge shaft of the right aileron; 44. the trailing edge of the right wing is vertical; 45. a battery installation compartment; 46. a heat insulating asbestos layer; 47. a stainless steel plate layer; 48. and (4) a fireproof paint layer.

Detailed Description

The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings, for the purpose of helping those skilled in the art to understand more completely, accurately and deeply the conception and technical solution of the present invention, and to facilitate its implementation.

It should be noted that, in the following embodiments, the terms "first", "second" and "third" do not denote absolute differences in structure and/or function, nor do they denote a sequential order of execution, but rather are used for convenience of description.

As shown in fig. 1 to 8, the utility model provides an electric aircraft battery packaging system, including set up in the inside battery installation cabin that just is used for holding the power battery module of wing, set up fire-extinguishing bottle 21 in the battery installation cabin, be connected with fire-extinguishing bottle 21 and stretch into the inside drainage tube 26 of power battery module and set up on the wing and be used for leading the air current to the inside air inlet unit of power battery module.

Specifically, as shown in fig. 1 and 2, the small electric airplane is a single-engine small airplane, and comprises a lower single wing (winglet), a low horizontal tail, two to four seats and a hatch door on the left and right. The power battery modules of the small electric airplane are respectively arranged inside two wings, the two wings are respectively a left wing 6 and a right wing 7, and the left wing 6 and the right wing 7 are symmetrically arranged. Three power battery modules are respectively arranged in the two wings, each power battery module contains an independent fire extinguishing bottle 21, and the fire extinguishing bottle 21 is used for extinguishing fire.

As shown in fig. 1, 3 to 5, the air intake device includes a main bleed air pipe 27 and a bleed air manifold 28 connected to the main bleed air pipe 27, the bleed air manifold 28 is provided in plurality and each bleed air manifold 28 is respectively inserted between two adjacent front-row battery blocks 32 of the power battery module, and the wing is provided with a ventilation bleed air port 29 for communicating the main bleed air pipe 27 with the external environment. The main bleed air pipe 27 has a certain length, the length direction of the main bleed air pipe 27 is parallel to the length direction of the wing, and all the bleed air manifolds 28 are arranged in sequence along the length direction of the main bleed air pipe 27. The ventilation bleed air ports 29 are funnel-shaped, and the ventilation bleed air ports 29 are located in the pressure area of the lower airfoil surface of the leading edge of the wing. The power battery module carries out air entraining through a funnel-shaped ventilation air entraining port 29 positioned in a pressure area of a lower wing surface of the front edge of the wing, air flow is divided left and right after entering the wing, enters each air entraining manifold 28 through an air entraining main pipe 27, and finally is guided into the power battery module through the air entraining manifolds 28. One end of the drainage tube 26 is connected with the fire extinguishing bottle 21, the other end of the drainage tube 26 is inserted into the power battery module, and when fire occurs, fire extinguishing foam in the fire extinguishing bottle 21 can be drained into the power battery module through the drainage tube 26.

As shown in fig. 1 and 3-6, the utility model discloses an electric aircraft battery packaging system is still including setting up on the wing and being used for carminative exhaust apparatus, and exhaust apparatus includes outlet manifold 30, and outlet manifold 30 sets up a plurality of and each outlet manifold 30 and inserts respectively between two adjacent back row battery pieces 31 of power battery module, sets up the air exit 33 that makes outlet manifold 30 and external environment communicate on the wing. The ventilation bleed air port 29 is positioned in the lower wing surface pressure area of the front edge of the right wing, and the exhaust port 33 is close to the rear edge of the wing.

As shown in fig. 1, 3 to 5, a plurality of power battery modules are arranged in the battery installation cabin, all the power battery modules are sequentially arranged along the length direction of the wing, and a fire extinguishing bottle 21 is arranged between every two adjacent power battery modules. The battery installation cabin is provided with a first rib 24 and a second rib 25, the first rib 24 and the second rib 25 are arranged in a plurality of positions, the first rib 24 and the second rib 25 are arranged at intervals, the fire extinguishing bottle 21 is positioned between the first rib 24 and the second rib 25, the second rib 25 is provided with a through hole for the drainage pipe 26 to pass through, and the power battery module is positioned between the second rib 25 and the other first rib 24. A front beam 22 and a rear beam 23 are arranged inside the wing, a first rib 24 and a second rib 25 are located between the front beam 22 and the rear beam 23, the first rib 24 and the second rib 25 are connected with the front beam 22 and the rear beam 23, and a fire extinguishing bottle 21 and a power battery module are located between the front beam 22 and the rear beam 23. The length directions of the front beam 22 and the rear beam 23 are parallel, the length directions of the front beam 22 and the rear beam 23 are parallel to the length direction of the wing, the front beam 22 and the rear beam 23 are sequentially arranged along the width direction of the wing, two ends of a first rib 24 are respectively and fixedly connected with the front beam 22 and the rear beam 23, two ends of a second rib 25 are respectively and fixedly connected with the front beam 22 and the rear beam 23, all the first ribs 24 are sequentially arranged along the length direction of the wing, all the second ribs 25 are sequentially arranged along the length direction of the wing, each first rib 24 is matched with each second rib 25 and surrounds the front beam 22 and the rear beam 23 to form a cavity for accommodating the fire-extinguishing bottle 21, the fire-extinguishing bottle 21 is fixed through a fire extinguisher mounting rack 35, and the fire extinguisher mounting rack 35 is fixedly arranged between the front beam 22 and the rear beam 23. The second rib 25 is located between two adjacent first ribs 24, and each power battery module is also located between one second rib 25 and one first rib 24. The power battery modules are respectively fixed on the front beams 22 and the rear beams 33 and the wing lower skin 40 through the mounting brackets 32, each power battery module comprises a front row battery block 32 and a rear row battery block 31, the front row battery blocks 32 are eight to twenty-four, the number of the rear row battery blocks 31 is the same as that of the front row battery blocks 32, and the number of the rear row battery blocks 31 is increased or decreased according to needs. The front row of battery blocks 32 is fixedly mounted on a battery mounting bracket 39, the battery mounting bracket 39 is fixedly connected with the front beam 22, all the front row of battery blocks 32 are sequentially arranged along the length direction of the front beam 22 and are distributed at equal intervals, and each bleed manifold 28 penetrates through the front beam 22 and is respectively inserted between every two adjacent front row of battery blocks 32. The rear row battery blocks 31 are fixedly mounted on a battery mounting bracket 39, the battery mounting bracket 39 is fixedly connected with the back beam 23, all the rear row battery blocks 31 are sequentially arranged along the length direction of the back beam 23 and are distributed at equal intervals, and the air outlet manifolds 30 penetrate through the back beam 23 and are respectively inserted between every two adjacent rear row battery blocks 31. The outlet manifolds 30 are provided in plurality, and all the outlet manifolds 30 are arranged in sequence along the length direction of the back beam 23 and are distributed at equal intervals. The rear beam 23 is parallel to the length direction of the drainage tube 26, the drainage tube 26 is positioned between the front row battery block 32 and the rear row battery block 31 of the power battery module, and the fire-extinguishing bottle stagnation valve 38 is installed on the drainage tube 26.

The ventilation of the power battery module is to bleed air through a bleed air main pipe 27, introduce air flow into the battery installation cabin through a bleed air manifold 28 between a plurality of front row battery blocks 32, and finally introduce the air flow through an air outlet manifold 30 between a plurality of rear row battery blocks 31, and finally flow out through an upper wing surface to take away the heat of the battery. The main bleed air pipe 27 is provided with a bleed air pipe stagnation valve 36, and the outlet manifold 30 is provided with an outlet manifold stagnation valve 37.

When the battery is overheated or a fire disaster is generated due to short circuit or other faults of the battery, a driver firstly closes the bleed air pipe stagnation valve 36 and the outlet manifold stagnation valve 37 through an instruction, and pinches off the air inlet and the air outlet to seal the battery installation cabin. At the same time, the stagnation valve 38 of the fire-extinguishing bottle on the drainage tube 26 is opened, and the drainage tube 26 guides the fire-extinguishing medium into the battery installation compartment for fire extinguishing.

As shown in fig. 5 to 7, the wing includes a wing lower skin 40, a wing upper skin 41 connected to the wing lower skin 40, and an upper skin cover plate 42 detachably connected to the front and

rear spars

22 and 23 and located above the battery compartment. The upper wing skin 41 is located above the lower wing skin 40, an opening for the power battery module to pass through is formed in the upper wing skin 41, and an upper skin cover plate 42 is used for closing the opening. The front beam 22 and the rear beam 23 are positioned between the upper wing skin 41 and the lower wing skin 40, the battery installation cabin is formed by surrounding an upper skin cover plate 42, the lower wing skin 40, the front beam 22 and the rear beam 23, the upper skin cover plate 42 is installed on the front beam 22 and the rear beam 23 through bolts, when the batteries are disassembled, inspected and replaced, the bolts connecting the upper skin cover plate 42 with the upper edge strips of the front beam 22 and the rear beam 23 are screwed out, and the front row batteries and the rear row batteries are taken out, so that the operation is convenient and simple.

As shown in fig. 7 and 8, in order to meet the fire-proof requirement, the bulkhead of the battery installation chamber needs to be specially treated, an insulating asbestos layer 46 is arranged on the bulkhead of the battery installation chamber, a stainless steel plate layer 47 is arranged on the insulating asbestos layer 46, and a fire-proof paint layer 48 is arranged on the stainless steel plate layer 47.

The electric aircraft battery packaging system with the structure can directly introduce cold air at the front edge of the wing in flight into the battery mounting cabin to ventilate and cool the battery, and meanwhile, the exhaust outlet is designed at the position, close to a transition point (laminar flow and turbulent flow transition), of the skin 41 on the wing, so that the kinetic energy of airflow of the skin 41 on the wing is increased while exhaust is carried out, the lift force of the wing in a large attack angle is improved, and the vortex area obviously moves towards the rear edge. Meanwhile, the battery is divided into three modules of the left wing and the right wing to be installed, each module is independently provided with the fire extinguishing bottle 21, and each battery module adopts an independent fire-proof bulkhead, so that the catastrophic consequences of the airplane caused by battery failure or fire are prevented, and the safety and reliability of the power battery of the airplane are improved.

The invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited by the above-described manner. Various insubstantial improvements are made by adopting the method conception and the technical proposal of the utility model; or without improvement, the above conception and technical solution of the present invention can be directly applied to other occasions, all within the protection scope of the present invention.

Claims

1. Electric aircraft battery packaging system, its characterized in that: including setting up in inside and being used for holding the battery installation cabin of power battery module of wing, setting up the fire bottle in the battery installation cabin, be connected with the fire bottle and stretch into the inside drainage tube of power battery module and set up on the wing and be used for leading the air current to the inside air inlet unit of power battery module.

2. The electric aircraft battery packaging system of claim 1, wherein: the air inlet device comprises an air guide main pipe and an air guide manifold connected with the air guide main pipe, the air guide manifold is provided with a plurality of air guide manifolds, each air guide manifold is respectively inserted between two adjacent front-row battery blocks of the power battery module, and a ventilation air guide port which enables the air guide main pipe to be communicated with the external environment is arranged on the wing.

3. The electric aircraft battery packaging system of claim 2, wherein: the power battery module is characterized by further comprising an exhaust device arranged on the wing and used for exhausting, the exhaust device comprises a plurality of air outlet manifolds, each air outlet manifold is inserted between two adjacent rear-row battery blocks of the power battery module, and an air outlet enabling the air outlet manifolds to be communicated with the external environment is formed in the wing.

4. The electric aircraft battery packaging system of claim 3, wherein: the ventilation bleed air inlet is positioned in the pressure area of the lower wing surface of the front edge of the right wing, and the air outlet is close to the rear edge of the wing.

5. The electric aircraft battery packaging system of any of claims 1 to 4, wherein: set up a plurality of power battery module in the battery installation cabin, all power battery modules are for arranging in proper order along the length direction of wing, the fire extinguishing bottle is arranged between every two adjacent power battery modules.

6. The electric aircraft battery packaging system of claim 5, wherein: set up first rib and second rib in the battery installation cabin, first rib and second rib all set up a plurality ofly and first rib and second rib are interval arrangement, the fire bottle is located between first rib and the second rib, and the second rib has and lets the through-hole that the drainage tube passed, and the power battery module is located between second rib and another first rib.

7. The electric aircraft battery packaging system of claim 6, wherein: the inside front-back beam and the back-back beam of setting up of wing, first rib with the second rib is located between front-back beam and the back-back beam and first rib and second rib are connected with front-back beam and back-back beam, fire extinguishing bottle and power battery module are located between front-back beam and the back-back beam.

8. The electric aircraft battery packaging system of claim 7, wherein: the front beam, the rear beam and the drainage tube are parallel in length direction, and the drainage tube is positioned between the front row of battery blocks and the rear row of battery blocks of the power battery module.

9. The electric aircraft battery packaging system of claim 7, wherein: the wing comprises a wing lower skin, a wing upper skin connected with the wing lower skin and an upper skin cover plate which is detachably connected with the front beam and the rear beam and is positioned above the battery installation cabin.

10. The electric aircraft battery packaging system of any of claims 1 to 4, wherein: the battery installation cabin is characterized in that a heat insulation asbestos layer is arranged on a cabin wall of the battery installation cabin, a stainless steel plate layer is arranged on the heat insulation asbestos layer, and a fireproof paint layer is arranged on the stainless steel plate layer.