CN-224217536-U - Cold and hot mixing device for electric aircraft

CN224217536UCN 224217536 UCN224217536 UCN 224217536UCN-224217536-U

Abstract

The utility model provides a cold and hot blending device of an electric airplane, which comprises a cold air collecting assembly, a mixing assembly and a heat dissipation assembly, wherein the mixing assembly is arranged above a battery assembly, the mixing assembly is provided with a mixing cavity, an outlet section of the mixing cavity is communicated with a cabin environment control system through a ventilation pipeline, the cold air collecting assembly comprises cold air pipelines, the number of the cold air pipelines is multiple, cold air inlets of the cold air pipelines are arranged on wings or a airplane body of the electric airplane and correspond to the battery assembly, cold air outlets of the cold air pipelines extend into an inlet section of the mixing cavity, the heat dissipation assembly comprises heat conducting coils, the number of the heat conducting coils is multiple and are all arranged on the bottom surface of the battery assembly, hot air inlets of the heat conducting coils are communicated with the battery assembly, and hot air outlets of the heat conducting coils extend into an inlet section of the mixing cavity and are arranged in a staggered manner with the cold air pipelines. The natural high-temperature air is fully utilized, the cold air and the hot air generated by the battery are fully mixed in the mixing cavity, the air temperature is effectively reduced, and the heat dissipation efficiency of the battery system is improved.

Inventors

YAN MENGRU
DONG JIE
GENG JINHONG

Assignees

西安奥若特材料技术有限公司

Dates

Publication Date: 20260508
Application Date: 20250428

Claims (9)

1. The cold and hot blending device for the electric aircraft is characterized by comprising a cold air collecting assembly, a mixing assembly and a heat dissipation assembly, wherein the mixing assembly is arranged above a battery assembly and is provided with a mixing cavity, an outlet section of the mixing cavity is communicated with a cabin environment control system through a ventilation pipeline, the cold air collecting assembly comprises a plurality of cold air pipelines, cold air inlets of the cold air pipelines are arranged on wings or a fuselage of the electric aircraft and correspond to the battery assembly, cold air outlets of the cold air pipelines extend into an inlet section of the mixing cavity, the heat dissipation assembly comprises heat conducting coils, the heat conducting coils are arranged on the bottom surface of the battery assembly, hot air inlets of the heat conducting coils are communicated with the battery assembly, and hot air outlets of the heat conducting coils extend into an inlet section of the mixing cavity and are staggered with the cold air pipelines.
2. The electric aircraft cold and hot blending device of claim 1, wherein the heat sink assembly further comprises a heat sink disposed on a bottom surface of the battery assembly, the heat conducting coil being disposed through the heat sink.
3. The cold and hot mixing device of an electric aircraft according to claim 1, wherein a heat insulation layer is arranged on the cold air pipeline, and a filter is arranged at a cold air inlet position of the cold air pipeline.
4. The electric aircraft cold and hot blending apparatus according to claim 1, wherein the height of the inlet section increases gradually in the air flow direction and the width of the outlet section decreases gradually in the air flow direction.
5. The cold and hot blending device of an electric aircraft according to claim 1, wherein a mixing section is arranged between the inlet section and the outlet section, a plurality of spoilers are arranged on the mixing section, air passing channels are formed in the spoilers, the spoilers are sequentially arranged along the air flow direction, and the channels of two adjacent spoilers are arranged in a staggered manner.
6. The electric aircraft cold and hot blending apparatus of claim 1, wherein the hybrid assembly is connected to the battery assembly by a thermal barrier.
7. The electric aircraft cold and hot blending apparatus according to claim 5, further comprising a flow control valve, a temperature sensor and a control module, wherein the flow control valve is respectively disposed on the cold air pipeline, the heat conducting disc pipeline and the ventilation pipeline, the temperature sensor is disposed at a position between the mixing section and the outlet section, and the flow control valve and the temperature sensor are respectively electrically connected with the control module.
8. The electric aircraft cold and hot blending device according to claim 7, wherein a driving pump electrically connected with the control module is arranged on the cold air pipeline.
9. The electric aircraft cold and hot blending device according to claim 7, wherein the cold air pipeline and the ventilation pipeline are provided with pressure sensors electrically connected with the control module.

Description

Cold and hot mixing device for electric aircraft Technical Field The utility model relates to the technical field of electric aircraft thermal management, in particular to a cold and hot blending device of an electric aircraft. Background With the development of aviation technology, electric aircrafts are receiving more and more attention as novel environment-friendly and efficient aircrafts. In the flight process of the electric aircraft, the battery system can generate a large amount of heat, if the heat is not dissipated in time, the battery performance is reduced, the service life is shortened, and even the safety problem is caused seriously. At present, application number is CN202321520754.0, discloses a power battery heat radiation structure for electric aircraft, including the battery module, the equal cladding all around of battery module has the panel, still includes water cooling subassembly, and water cooling subassembly includes the water cooling pipeline, the water cooling pipeline sets up between battery module and panel, the panel outside is hugged closely and is provided with wind channel heat radiation assembly, water cooling subassembly extend to the panel outside with air cooling heat radiation assembly communicates with each other, provides the hydrologic cycle driving force by the water pump. Through set up the water-cooling pipeline in the battery module inside, the outside sets up forced air cooling subassembly to make water-cooling subassembly and forced air cooling subassembly communicate with each other, through water pump drive hydrologic cycle power, can derive the heat energy that the electric core produced fast to fan cooling subassembly, by fan cooling subassembly heat dissipation with higher speed, effectively reduce the intensification of electric core under the high multiplying power discharge operating mode in the short time. Although the disclosed patent solves the problem of battery heat dissipation to a certain extent by combining water cooling and air cooling, under the special application scene of the electric aircraft, the technical problems still exist that the prior art mainly depends on the internal circulation of the water cooling and air cooling heat dissipation assembly, drives the water circulation through a water pump, and relies on the fan heat dissipation assembly to accelerate heat dissipation, and the heat dissipation process needs additional large amount of energy consumption, so that the whole energy consumption of the electric aircraft is further increased, and the realization of the energy saving and emission reduction targets of the electric aircraft is not facilitated. Moreover, during high-altitude flight, a large amount of low-temperature cold air exists around the electric aircraft, but most of the existing battery heat dissipation means cannot effectively utilize the high-temperature cold air, so that energy waste and low heat dissipation efficiency are caused. In addition, the air cooled by the fan still remains in the electronic cabin and is not further reasonably utilized. Therefore, how to effectively utilize high-altitude air resources in the flight process of the electric aircraft and realize the rapid heat dissipation and the efficient heat management of the battery system becomes a technical problem to be solved in the field of electric aircraft heat management. In view of this, the present utility model has been made. Disclosure of utility model The utility model aims to provide a cold and hot mixing device for an electric airplane, which aims to solve the problems that the heat dissipation design of a battery module of the electric airplane in the prior art has defects, and the natural cold source of high-temperature air cannot be fully utilized, so that energy waste and low heat dissipation efficiency are caused. The preferred technical solutions of the technical solutions provided by the present utility model can produce a plurality of technical effects described below. In order to achieve the above purpose, the present utility model provides the following technical solutions: The utility model provides a cold and hot blending device of an electric airplane, which comprises a cold air collecting assembly, a mixing assembly and a heat dissipation assembly, wherein the mixing assembly is arranged above a battery assembly, the mixing assembly is provided with a mixing cavity, an outlet section of the mixing cavity is communicated with a cabin environment control system through a ventilation pipeline, the cold air collecting assembly comprises a plurality of cold air pipelines, cold air inlets of the cold air pipelines are arranged on a wing or a airplane body of the electric airplane and correspond to the battery assembly, cold air outlets of the cold air pipelines extend into an inlet section of the mixing cavity, the heat dissipation assembly comprises a plurality of heat conducting coils, the heat conducting coils are arranged on the