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Aircraft and structure battery component of aircraft

An aircraft and battery technology, applied to aircraft parts, chords/stringers, transportation and packaging, etc., can solve the problems of less charge and discharge cycles, capacitance attenuation, and severe battery volume expansion, etc., to reduce strength/rigidity constraints , reduce weight, reduce the effect of trim constraints

Inactive Publication Date: 2019-05-17
中国兵器工业导航与控制技术研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Lithium-sulfur batteries are used as secondary batteries on existing solar-powered drones. Lithium-sulfur batteries have problems such as lithium polysulfide shuttle effect, severe battery volume expansion, serious capacity attenuation, and relatively few charge-discharge cycles, which are not as good as alkaline nickel. Base secondary batteries and lithium-ion secondary batteries are safe and reliable

Method used

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  • Aircraft and structure battery component of aircraft
  • Aircraft and structure battery component of aircraft
  • Aircraft and structure battery component of aircraft

Examples

Experimental program
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Effect test

specific Embodiment approach 1

[0070] like Figure 5 As shown, the functional laminate 25 includes an anode 31, a diaphragm 32 and a cathode 33; the first layer structure and the third layer serve as the anode 31 and cathode 33 of the battery respectively, and the middle layer structure serves as the diaphragm 32 of the battery.

[0071] (Each layer is a prepreg. The prepreg is a fabric prepreg, that is, there are first fibers 51 in the anode, third fibers 53 in the cathode, and second fibers 55 in the separator 32)

[0072] The anode includes an anode matrix 52 and first fibers 51 in the anode matrix; the cathode includes a cathode matrix and third fibers 53 in the cathode matrix; the membrane 32 includes a membrane matrix 21 and second fibers 55 in the membrane.

[0073] The anode (polymer) matrix 52 of the anode, the membrane (polymer) matrix 56 of the membrane, and the cathode (polymer) matrix 54 of the cathode are all electrically insulating. Can be epoxy, rubber or a resin-rubber mixture. Other poly...

specific Embodiment approach 2

[0082]The functional laminate 25 includes an anode 31 , a separator 32 and a cathode 33 .

[0083] The anode 31 is a fiber bundle or several fiber bundles not in contact with each other, and the fiber bundle is a fiber filament or a plurality of fiber filaments with electrical conductivity.

[0084] Diaphragm 32 is a solid polymer electrolyte on the periphery of anode 31; it can be coated on the periphery of anode 31.

[0085] The cathode 33 is a polymer matrix containing electrochemically active substances and is connected to a metal current collector.

[0086] like Image 6 Shown, a plurality of conductive fiber bundles, coated with a solid polymer electrolyte; immersed in a polymer matrix containing electrochemically active particles.

[0087] The anode of the battery is directly used as a current collector or connected to a metal current collector (the current collector is in Image 6 not shown in). The number and arrangement of fiber bundles are not limited to Image...

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Abstract

The invention provides an aircraft and a structure battery component of the aircraft, and belongs to the technical field of the aircraft overall design. The structure battery component can play the function of bearing force and / or storing power at the same time, thereby effectively reducing the total weight when the structure and the battery are mutually independent; the structure battery component can be applied to the aircraft to realize the weight reducing of the aircraft structure system and the battery system. The aircraft is the aircraft with the structure battery component; one structure battery component comprises wing ribs on at least two ends and skin at the periphery; the wing rigs are arranged at two ends of the skin; the skin is at least a multi-layer board with one function overlay; the function overlay has a bearing function, and further has a power supply and / or power storage function; the designability of the composite material structure is sufficiently utilized, the force-bearing structure and the power supply and / or power storage battery are integrated; the structure battery component with the force-bearing, the power supply and / or power storage functions is usedfor realizing the lightweight of the aircraft, and more task load weight can be gotten in return, and the aircraft performance is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft overall design, and relates to an aircraft with structural battery components. Background technique [0002] Existing aircraft includes two independent subsystems of structure and power supply. The structural subsystem acts as a load-bearing function, so that the aircraft has sufficient strength and rigidity to resist external loads; the power supply subsystem is used to maintain the normal operation of flight control, electronic equipment and even power propulsion subsystems. [0003] Structural subsystems and power supply subsystems should reduce weight as much as possible to improve aircraft performance under the premise of meeting their own functional constraints. In order to achieve light weight, more and more composite laminates are used in the structure of existing aircraft, but the layers of laminates do not contain electrochemically active substances, so the structure itself does not ha...

Claims

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Application Information

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IPC IPC(8): B64C3/18B64C3/26
Inventor 黄超李跃军朱辉南雪飞杨享文席柯高永姜宝森
Owner 中国兵器工业导航与控制技术研究所
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