US 12,030,628 B2
Crash detection device, flying body crash detection method, parachute or paraglider deployment device, and airbag device
Hiroshi Nakamura, Tokyo (JP); Yasuhiko Yagihashi, Tokyo (JP); and Koichi Sasamoto, Tokyo (JP)
Appl. No. 16/756,583
Filed by NIPPON KAYAKU KABUSHIKI KAISHA, Tokyo (JP)
PCT Filed Oct. 11, 2018, PCT No. PCT/JP2018/038008
§ 371(c)(1), (2) Date Apr. 16, 2020,
PCT Pub. No. WO2019/078094, PCT Pub. Date Apr. 25, 2019.
Claims priority of application No. 2017-200320 (JP), filed on Oct. 16, 2017.
Prior Publication US 2020/0239136 A1, Jul. 30, 2020
Int. Cl. B64C 39/02 (2023.01); B64D 17/54 (2006.01); B64D 25/00 (2006.01); G05B 23/02 (2006.01); G05D 1/00 (2006.01); B64U 10/13 (2023.01)
CPC B64C 39/02 (2013.01) [B64D 17/54 (2013.01); B64D 25/00 (2013.01); G05B 23/0205 (2013.01); G05D 1/0055 (2013.01); G05D 1/0066 (2013.01); B64U 10/13 (2023.01)] 5 Claims
OG exemplary drawing
 
1. A crash detection device for mounting on a flying object having a parachute or paraglider deployment device, the crash detection device comprising:
a sensor configured for measuring a parameter related to a flying state of the flying object, said sensor is configured for acquiring data of said parameter in a normal mode in which the data is acquired at a sampling frequency of less than 1 kHz, and in an abnormal mode in which the data is acquired at the sampling frequency of 1 kHz or more;
a detector coupled to said sensor and configured for verifying proper operation of said sensor; and
a controller configured for receiving from said sensor values of said parameter and for determining flying state of the flying object;
wherein said controller is configured to selectively shift from said normal mode to said abnormal mode when data of said parameter is above a predetermined threshold value and said proper operation of said sensor is verified by said detector;
wherein said controller is further configured to determine an abnormal flying state in accordance with data obtained from said sensor in said abnormal mode and to output an activation signal for actuating the deployment device in response to said abnormal flying state; and
wherein the controller is configured to distinguish noise based on information on a half width or a peak area of a peak of the data acquired by calculating the data acquired from the sensor.