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XIAN AEROSPACE PROPULSION INST

Overview
  • Total Patents
    357
  • GoodIP Patent Rank
    4,158
  • Filing trend
    ⇧ 133.0%
About

XIAN AEROSPACE PROPULSION INST has a total of 357 patent applications. It increased the IP activity by 133.0%. Its first patent ever was published in 2017. It filed its patents most often in China. Its main competitors in its focus markets engines, pumps and turbines, measurement and mechanical elements are AKTSIONERNOE OBSHCHESTVO KONST BYURO KHIMAVTOMATIKI, SPACEFLIGHT KEGONG ROCKET TECH CO LTD and SHANGHAI XINLI POWER EQUIPMENT INST.

Patent filings in countries

World map showing XIAN AEROSPACE PROPULSION INSTs patent filings in countries
# Country Total Patents
#1 China 357

Patent filings per year

Chart showing XIAN AEROSPACE PROPULSION INSTs patent filings per year from 1900 to 2020

Top inventors

# Name Total Patents
#1 Li Guangxi 25
#2 Hu Bo 17
#3 Xu Kaifu 16
#4 Chen Hongyu 16
#5 Gao Yushan 16
#6 Shi Hongbin 14
#7 Xi Keqing 14
#8 Wang Zhe 14
#9 Qin Hongqiang 13
#10 Liang Junlong 13

Latest patents

Publication Filing date Title
CN112267957A Pintle type injector capable of realizing accurate adjustment
CN112282964A High-thrust engine for aircraft
CN112278241A Helicopter propeller system based on magnetic constraint force
CN112229268A Recoil measuring mechanism for portable launcher launching cartridge missile
CN112196698A Non-full-circumference opening flow-limiting boosting type one-way valve
CN112282971A Solid gas starter for gas self-pressurization
CN112268366A Pressure bearing container of heat accumulating type heater
CN112240719A Hollow brick heat accumulator structure and heat accumulation type heater
CN112240570A Swirl torch igniter based on 3D printing forming
CN112196753A CO (carbon monoxide)2Injection pump system
CN112072890A Voice coil motor structure with ultra-small volume
CN112012853A Solid rocket engine of back skirt connection form thrust transmission device for ignition test
CN112039309A Voice coil motor magnetic circuit structure
CN112083039A Material ignition point test assessment device and method
CN112177800A Cooling structure for spiral wheel pair bearing of liquid rocket engine pump
CN112253334A Gas pipeline integrated with cooling channel
CN112066070A Variable flow electromagnetic pilot control valve
CN112160851A High-sealing low-combustion-temperature detachable gunpowder starter
CN112196632A Prepressing turbine inlet shell and machining method thereof
CN112066116A Spherical sealing joint for hydraulic test of turbopump of liquid rocket engine