Attitude sensing system

• US 4,754,280 A
• Filed: 09/10/1982
• Issued: 06/28/1988
• Est. Priority Date: 09/10/1982
• Status: Expired due to Term

• Current Assignee: Charles Stark Draper Laboratory Incorporated
• Original Assignee: Charles Stark Draper Laboratory Incorporated
• Inventors: Thorvaldsen, Tom P., Brown, Alison K., Bowles, W. Michael
• Primary Examiner(s): Blum, Theodore M.
• Assistant Examiner(s): Issing, Gregory C.
• Application Number:
  US06/416,646
• Time in Patent Office: 2,118 Days
• Field of Search: 343/357, 343/394, 343/424, 343/420, 343/356, 343/396, 343/352, 318/580-582, 318/648, 318/649
• US Class Current: 342/357.59
• CPC Class Codes: G01S 19/54 using carrier phase measurements; using long or short baseline interferometry

Abstract

An attitude sensing system which incorporates the precision in attitude sensing of a satellite navigation system with the dynamic tracking capabilities of an inertial measurement unit. Optimally estimated attitude and system error signals are combined with the outputs of an inertial measurement unit to control the phase differences of signals received on an interferometer array from a navigation satellite. The outputs from the inertial measurement unit and the phase differences are processed in an optimal estimator filter to produce periodically updated attitude and system error signals. This permits inertial attitude sensing to benefit from the long term accuracy of attitude estimation based upon signals from the satellite navigation system. During conditions of high dynamic maneuvering in which attitude changes are rapid, the output of the inertial measurement unit continues to provide attitude information and controls the attitude sensing loop to insure that the system is not disoriented by such high dynamic conditions.

Claims

1. An attitude sensing system comprising:

a satellite receiver operative to respond on an interferometric array of receiving antennas to satellite generated signals to provide a plurality of output signals representative of the phase difference in signals received between plural ones of said antennas and reflecting relative attitudes between said array and the satellite;

an inertial measurement unit positionally associated with said satellite receiver and operative to provide an output representing an attitude vector of said sensing system in inertial space; and

means for combining said output signals from said satellite receiver and said output from said inertial measurement unit for adjusting said inertial measurement unit output with attitude information from the satellite, wherein

said satellite receiver includes;

at least three antennas physically separated from each other and each receiving a signal from one or more navigation satellites with a phase characteristic of the attitude of said three antennas relative to said navigation satellite;

a plurality of phase comparing loops each responsive to the output of two of said plural antennas for each satellite and operative to provide an adjustment in the phase of the output of one said antenna relative to the other tending to reduce the phase difference therebetween and to produce an error output signal representative of remaining phase difference;

a digital filter responsive to the phase error output of each phase comparing loop to provide an estimate of attitude of said three or more antennas relative to said satellite and a vector error estimate signal; and

delay correction means for providing a phase error estimate signal in response to said vector error estimate signal, wherein

each said phase comparing loop is responsive to at least said phase error estimate signal to provide adjustment in said phase comparing loops tending to reduce the remaining phase difference between the signals from the two antennas applied thereto.

2. The system of claim 1 wherein said combining means includes means for identifying errors of said inertial measurement unit and for providing corrections therefore in said output of said inertial measurement unit.

3. The system of claim 1 wherein:

said combining means is further operative to provide outputs representative of gyroscope errors; and

means are provided, in response to said gyroscope error outputs, to provide calibration of said inertial measurement unit output tending to reduce the effect of said errors therein.

4. The system of claim 1 wherein

said combining means includes means for providing an initial phase adjustment in response to received satellite position data and estimated system position.

5. An attitude sensing system comprising:

an inertial measurement unit providing an attitude representing output;

a satellite receiver receiving satellite signals on an array of antennas to provide signals representing phase differences between each antenna of said array; and

digital filter means operative in response to said attitude representing output and said phase difference signals to provide a state signal and a phase error estimate signal periodically updated as a function of said phase difference signals and between updates as a function of the attitude signal and said state signal at the last update wherein,

said phase error estimate signal is received by said satellite receiver for adjusting signals representing phase differences between each antenna of said array.