CN-121983732-A - Electric aircraft power battery compartment system and cooperative control method thereof

Abstract

The invention discloses an electric aircraft power battery compartment system and a cooperative control method thereof. The system comprises a battery module, an airtight shell wrapping the battery module to form a main sealing cavity, and helium filled in the cavity. The system is also provided with an emergency air film layer and an arc extinguishing nozzle array which are respectively connected with a helium source through control valves. The control unit controls helium to be maintained at a first pressure in a normal state according to monitoring data of the sensor module so as to simultaneously provide buoyancy compensation and vibration isolation of the gas spring, and when the impact condition is met, the helium is injected into the emergency gas film layer to be boosted so as to form impact resistance buffer, and when the short circuit condition is met, the helium is released from the nozzle so as to inhibit electric arcs. The invention realizes the integrated integration of buoyancy weight reduction, vibration isolation, impact buffering and electric safety protection.

Inventors

• CHENG LIN
• HE QIANG
• ZHANG XUXIN
• YANG XIAOQIANG

Assignees

• 中国民用航空飞行学院

Dates

Publication Date

20260505

Application Date

20260209

Claims (10)

1. 1. An electric aircraft power battery compartment system, comprising: a battery module; an airtight housing wrapping the battery module to form a main sealed cavity; helium filled in the main sealing cavity; The sensor module is used for monitoring the electrical state of the battery module and the impact state of the battery compartment system; The control unit is in communication connection with the sensor module and is used for controlling the opening and closing of the first control valve and the second control valve according to the monitoring data of the sensor module; The emergency air film layer is arranged on the airtight shell and is connected with a helium source through a first control valve; The arc extinguishing nozzle array is arranged in the battery cell lug area and the main electrical connection point of the battery module and is connected with a helium source through a second control valve.
2. 2. The power cell compartment system of claim 1, wherein the airtight housing is made of an aluminum plastic composite film.
3. 3. The power cell compartment system of claim 1, further comprising a hollowed-out support frame disposed between the airtight housing and the battery module.
4. 4. The power cell compartment system of claim 1, wherein the emergency air film layer is disposed adjacent the primary seal cavity and collectively comprises a double-layer air film structure.
5. 5. A method of cooperative control of an electric aircraft power battery compartment, characterized in that it is performed on the basis of a control unit of a system according to any one of claims 1 to 4, the method comprising: Under normal flight conditions, maintaining helium in the main seal cavity at a first pressure to simultaneously provide buoyancy compensation and isolate fuselage vibrations based on gas spring effects; When the sensor module monitors that a preset impact triggering condition is met, helium is controlled to be injected into the emergency air film layer, so that the pressure of the helium is increased to a second pressure higher than the first pressure, and impact-resistant buffering is formed; and when the sensor module monitors that the preset short-circuit triggering condition is met, controlling helium to be released from the arc extinguishing nozzle array so as to inhibit electric arcs.
6. 6. The method of claim 5, wherein maintaining helium pressure during normal flight conditions comprises: determining a buoyancy compensation target according to the design index and the mission profile of the electric aircraft, and configuring the volume of the main sealing cavity and the first pressure according to the buoyancy compensation target; And acquiring the vibration source characteristics of the electric aircraft, and adjusting the first pressure to enable the natural frequency of the vibration isolation system formed by the main sealing cavity to avoid the main frequency in the vibration source characteristics.
7. 7. The method of claim 5, wherein the predetermined shock triggering condition is that the shock acceleration monitored by the sensor module exceeds a first threshold and the sinking rate exceeds a second threshold.
8. 8. The method of claim 5, wherein after the step of controlling the injection of helium into the emergency gas film is completed, the helium in the emergency gas film is slowly depressurized by a throttling structure.
9. 9. The method of claim 5, wherein the step of controlling the release of helium gas upon detecting that a preset short trigger condition is satisfied comprises first controlling the main power supply circuit of the battery module to be shut off, and then controlling the second control valve to be opened to release helium gas.
10. 10. The method of claim 5, wherein the predetermined short trigger condition is the rate of change of battery current monitored by the sensor module exceeding a third threshold or the battery voltage drop exceeding a fourth threshold.

Description

Electric aircraft power battery compartment system and cooperative control method thereof Technical Field The invention belongs to the field of battery compartments of electric aircrafts, and particularly relates to a power battery compartment system of an electric aircraft and a cooperative control method thereof. Background The power supply system is a key support for the electric aircraft to realize the core flight performances of hovering, forward flying, climbing, cruising and the like, and the self weight and the safety reliability of the electric aircraft directly determine the task adaptability and the operation feasibility of the whole aircraft. Periodic vibration of the machine body can be generated in the flight process of the electric aircraft, and then the problems of loose battery connection, short circuit, fire and the like are caused. How to more effectively reduce the weight of the battery, isolate the vibration of the fuselage and restrain the thermal runaway of the battery is a core requirement of the design of the battery compartment of the aircraft. The good battery compartment design has the structure and the active protection function, and is an important supporting system for ensuring the efficient and reliable operation of the power battery. Current electric aircraft battery compartment designs focus on structural strength, stiffness, and thermal management, often with structural shell packaging in combination with heat dissipation or heating schemes. Although the design can ensure basic functions under normal flight conditions, the design has obvious defects when in extreme working conditions such as thermal runaway, short circuit arcing, crash and the like. Current battery compartment designs fail to achieve effective vibration protection to prevent accelerated cyclic aging of the battery, lack active thermal runaway suppression and arc extinction, and do not have the ability to mitigate battery weight and impact damage. The traditional passive safety design mode cannot adapt to the dynamic requirements of complex flight tasks and performances of the aircraft, the safety and reliability improvement of a battery compartment is severely limited, and the risk of flight accidents caused by battery faults is possibly increased. Disclosure of Invention In order to solve the technical problems, the invention provides an electric aircraft power battery compartment system, which comprises: a battery module; an airtight housing wrapping the battery module to form a main sealed cavity; helium filled in the main sealing cavity; The sensor module is used for monitoring the electrical state of the battery module and the impact state of the battery compartment system; The control unit is in communication connection with the sensor module and is used for controlling the opening and closing of the first control valve and the second control valve according to the monitoring data of the sensor module; The emergency air film layer is arranged on the airtight shell and is connected with a helium source through a first control valve; The arc extinguishing nozzle array is arranged in the battery cell lug area and the main electrical connection point of the battery module and is connected with a helium source through a second control valve. Optionally, the airtight shell is made of an aluminum-plastic composite film. Optionally, the battery module further comprises a hollowed-out supporting framework arranged between the airtight shell and the battery module. Optionally, the emergency air film layer is adjacent to the main sealing cavity to form a double-layer air film structure. The invention also provides a cooperative control method of the power battery compartment of the electric aircraft, which is executed based on a control unit of the system, and comprises the following steps: Under normal flight conditions, maintaining helium in the main seal cavity at a first pressure to simultaneously provide buoyancy compensation and isolate fuselage vibrations based on gas spring effects; When the sensor module monitors that a preset impact triggering condition is met, helium is controlled to be injected into the emergency air film layer, so that the pressure of the helium is increased to a second pressure higher than the first pressure, and impact-resistant buffering is formed; and when the sensor module monitors that the preset short-circuit triggering condition is met, controlling helium to be released from the arc extinguishing nozzle array so as to inhibit electric arcs. Optionally, the step of maintaining helium pressure during normal flight conditions includes: determining a buoyancy compensation target according to the design index and the mission profile of the electric aircraft, and configuring the volume of the main sealing cavity and the first pressure according to the buoyancy compensation target; And acquiring the vibration source characteristics of the electric aircraft, and adjusting the first