Crash detection device, flying body crash detection method, parachute or paraglider deployment device, and airbag device

Patent metadata

Field	Value
Publication number	US-12030628-B2
Application number	US-201816756583-A
Country	US
Kind code	B2
Filing date	Oct 11, 2018
Priority date	Oct 16, 2017
Publication date	Jul 9, 2024
Grant date	Jul 9, 2024

Abstract

A crash detection device for mounting on a flying object having a parachute or paraglider deployment device. The crash detection device includes a sensor for measuring a parameter related to a flying state of the flying object. The sensor is configured for acquiring data of the 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. The crash detection device further includes a detector coupled to the sensor and configured for verifying proper operation of the sensor; and a controller configured for receiving from the sensor values of the parameter and for determining flying state of the flying object.

First claim

The invention claimed is:

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.

2. The crash detection device according to claim 1 , wherein in an initial state said sensor is configured for acquiring data of said parameter in a normal mode.

3. A parachute or paraglider deployment device comprising:
the crash detection device described in claim 1 ,
a parachute or a paraglider that is deployable; and an ejection device that, when an abnormal signal is output by the crash detection device, receives the abnormal signal and ejects the parachute or the paraglider.

4. An airbag device comprising:
an airbag that is inflatable;
the crash detection device described in claim 1 ; and
a gas generator that, when an abnormal signal is output by the crash detection device, receives the abnormal signal and supplies gas into the airbag.

5. A method of detecting a crash of a flying object, the flying object including a safety device, the method comprising:
a data acquisition step of acquiring from a sensor data of a flying state of the flying object at a sampling frequency of 1 kHz or more;
a detection step of verifying proper operation of the sensor;
a first determination step of determining whether the data acquired in the data acquisition step is equal to or greater than a predetermined threshold value;
a second determination step of determining whether the data is data indicating that the flying state of the flying object is abnormal or noise that is unnecessary data when the data is determined to be equal to or greater than the predetermined threshold value by the first determination step, said second determination step further includes distinguishing 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; and
a step of activating the safety device by the second determination step when the data is determined to be the data indicating that the flying state of the flying object is abnormal.

Assignees

• Nippon Kayaku Kk

Inventors

• Nakamura Hiroshi
• Yagihashi Yasuhiko
• Sasamoto Koichi

Classifications

• G05D1/83

  Limitation of acceleration or structural stress · CPC title

• G05D1/617

  Safety or protection, e.g. defining protection zones around obstacles or avoiding hazards (arrangements for controlling the position or course of two or more vehicles for avoiding collisions therebetween G05D1/693; arrangements for reacting to or preventing system or operator failure G05D1/80) · CPC title

• B64U10/13

  Flying platforms · CPC title

• B64U20/83

  Electronic components structurally integrated with aircraft elements, e.g. circuit boards carrying loads · CPC title

• B64U70/83

  using parachutes, balloons or the like · CPC title