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Aircraft Attitude Determination Using GPS

技術優勢

The new UC technology provides the following benefits: Drastically improves the performance of the navigation system without requiring additional hardware and algorithm; Provides estimation of all other aircraft states, such as position, velocity, and angular rates, without the need for multiple gyros or accelerometers on board.

技術應用

This new UC technology has applications in aircraft navigation instrumentation.

詳細技術說明

Scientists at the University of California have developed a new instrument that is capable of accurately estimating all aircraft states, such as position, attitude, velocity, and angular rates. This system can provide the aircraft attitude over the flight envelope and in different exogenous weather conditions by using only the input from a single GPS receiver and the aircraft dynamics.

*Abstract

None

*IP Issue Date

Jun 17, 2003

*Principal Investigation

Name: Laurence Helen Mutuel

Department:

Name: Jason Speyer

Department:

附加資料

Patent Number: US6580389B2
Application Number: US2001928099A
Inventor: Speyer, Jason L. | Mutuel, Laurence H.
Priority Date: 11 Aug 2000
Priority Number: US6580389B2
Application Date: 10 Aug 2001
Publication Date: 17 Jun 2003
IPC Current: G01C002116 | G01S000502 | G01S000514 | G01S001921 | G01S001926 | G01S001948 | G01S001949 | G01S001951 | G05D000108
US Class: 34235731 | 34235711
Assignee Applicant: The Regents of the University of California
Title: Attitude determination using a global positioning system
Usefulness: Attitude determination using a global positioning system
Summary: Determining aircraft attitude using GPS.
Novelty: Attitude determination for vehicle orientation determination using GPS supplied position and velocity information and vehicle dynamics information from Kalman filter

主要類別

汽車

細分類別

輔助駕駛

申請號碼

6580389

其他

BACKGROUND

Global Positioning System (GPS) technology has come into widespread use and is now becoming a preferred instrument for high accuracy position and velocity estimation in inertial space. However, a stand-alone GPS receiver cannot estimate the attitude of an aircraft and must be coupled with an inertial instrument or use multiple antennas to obtain this information. The result of these additions is an increased cost in hardware and complexity of the navigation system.

Additional Technologies by these Inventors

• A New Peak-Seeking Control Method

Tech ID/UC Case

10207/2000-485-0

Related Cases

2000-485-0

國家/地區

美國