公开(公告)号：US07623068B2

公开(公告)日：2009-11-24

申请号：US11749603

申请日：2007-05-16

Applicant: Luke Stephen Powell ,  Thomas Howard Jaeckle

Inventor： Luke Stephen Powell ,  Thomas Howard Jaeckle

IPC: G01S1/02

CPC classification number: G01S19/01 ,  G01S19/14 ,  G01S19/20 ,  G01S19/21

Abstract: A method for detecting the presence of a deception signal associated with a satellite navigation system. The deception signal has certain “observables”, which can be used by a GPS receiver to detect the presence of the deception signal.

Abstract translation: 一种用于检测与卫星导航系统相关联的欺骗信号的存在的方法。 欺骗信号具有一定的“可观测值”，GPS接收机可以使用这些“可观察”来检测欺骗信号的存在。

公开(公告)号：US20080169978A1

公开(公告)日：2008-07-17

申请号：US11749603

申请日：2007-05-16

Applicant: Luke Stephen Powell ,  Thomas Howard Jaeckle

Inventor： Luke Stephen Powell ,  Thomas Howard Jaeckle

IPC: G01S1/00

CPC classification number: G01S19/01 ,  G01S19/14 ,  G01S19/20 ,  G01S19/21

Abstract: A method for detecting the presence of a deception signal associated with a satellite navigation system. The deception signal has certain “observables”, which can be used by a GPS receiver to detect the presence of the deception signal.

Abstract translation: 一种用于检测与卫星导航系统相关联的欺骗信号的存在的方法。 欺骗信号具有一定的“可观测值”，GPS接收机可以使用这些“可观察”来检测欺骗信号的存在。

公开(公告)号：US06609680B2

公开(公告)日：2003-08-26

申请号：US09862507

申请日：2001-05-23

Applicant: William Dean Perry ,  Thomas Howard Jaeckle ,  Allan Bernard Black ,  Lawrence Ernest Epley

Inventor： William Dean Perry ,  Thomas Howard Jaeckle ,  Allan Bernard Black ,  Lawrence Ernest Epley

IPC: B64B102

CPC classification number: B64B1/62 ,  B64B1/02 ,  B64B1/30 ,  B64B1/38 ,  B64B1/58 ,  B64B1/60 ,  B64B1/70

Abstract: A high-altitude airship has a non-rigid hull. On launch, the airship is partially inflated with a lifting gas. The partially inflated hull is less susceptible to buffeting and turbulence from lower atmosphere air currents during ascent. A ballast rotates the airship into a flight attitude (e.g., near horizontal) upon reaching a desired altitude. A low-powered propulsion system may be included to propel the airship at the desired altitude. Upon completion of its mission, the airship may be deflated and returned using aerodynamic deceleration such as a parachute, a parafoil and a ballute.

公开(公告)号：US11300687B2

公开(公告)日：2022-04-12

申请号：US16846350

申请日：2020-04-12

Applicant: Thomas Howard Jaeckle ,  Wayne D. Music ,  Donald R. Van Rheeden ,  Thomas Tillotson ,  Jeffery C. Sanders

Inventor： Thomas Howard Jaeckle ,  Wayne D. Music ,  Donald R. Van Rheeden ,  Thomas Tillotson ,  Jeffery C. Sanders

IPC: G01S19/21 ,  H04K3/00 ,  G01S19/43 ,  G01S19/27 ,  G01S19/01

Abstract: A system and method for discriminating and mitigating spoofing signals incoming to a satellite navigation system. Beam steering techniques are used to steer a null toward a legitimate satellite signal that is being spoofed. The spoofing signal is then tracked and its angle of arrival measured. A null is steered toward the measured angle of arrival of the spoofing signal, and the spoofing signal is confirmed by determining if there is a signal remaining with nulls on both the legitimate satellite signal and the spoofing signal. The null toward the legitimate satellite signal is then replaced with unity gain.

公开(公告)号：US20210318447A1

公开(公告)日：2021-10-14

申请号：US16846350

申请日：2020-04-12

Applicant: Thomas Howard Jaeckle ,  Wayne D. Music ,  Donald R. Van Rheeden ,  Thomas C. Tillotson ,  Jeffery C. Sanders

Inventor： Thomas Howard Jaeckle ,  Wayne D. Music ,  Donald R. Van Rheeden ,  Thomas C. Tillotson ,  Jeffery C. Sanders

IPC: G01S19/21 ,  G01S19/01 ,  G01S19/27 ,  G01S19/43

Abstract: A system and method for discriminating and mitigating spoofing signals incoming to a satellite navigation system. Beam steering techniques are used to steer a null toward a legitimate satellite signal that is being spoofed. The spoofing signal is then tracked and its angle of arrival measured. A null is steered toward the measured angle of arrival of the spoofing signal, and the spoofing signal is confirmed by determining if there is a signal remaining with nulls on both the legitimate satellite signal and the spoofing signal. The null toward the legitimate satellite signal is then replaced with unity gain.