Procedure for measuring angles and trajectories by means of gyros and inertial systems

• US 5,331,578 A
• Filed: 09/11/1991
• Issued: 07/19/1994
• Est. Priority Date: 09/14/1990
• Status: Expired due to Fees

• Current Assignee: Deutsche Telekom AG
• Original Assignee: Deutsche Telekom AG
• Inventors: Stieler, Bernhard F. M.
• Primary Examiner(s): Harvey, Jack B.
• Assistant Examiner(s): Wachsman, Hal D.
• Application Number:
  US07/757,842
• Time in Patent Office: 1,042 Days
• Field of Search: 364/571.01, 364/571.02, 364/571.04, 364/571.05, 364/571.07, 364/551.01, 364/559, 364/453, 364/454, 364/443, 364/449, 33/1 N, 33/312, 33/313, 33/318-324, 73/1 E, 73/865.8, 73/866.5
• US Class Current: 702/93
• CPC Class Codes: E21B 47/022 of the borehole, e.g. using geomagnetism
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems
• CPC Class Codes: G01C 25/005 initial alignment, calibration or starting-up of inertial devices

Abstract

The calibration of time-depending measurement uncertainties of gyros and inertial systems by the differences of angular and/or velocity and/or positional measurements which are carried out and repetitiously executed with a view to undetermined reference directions and/or fixed locations varying with time. The differentiation allows to forego precise reference data. Measurement uncertainties can be corrected through calibration subsequently to the measurement process. For the measurement of spatial angles a three-axis gyro measurement package comprising a computer and the possibility of feeding or automaticly reading-in of reference data characterizing the reference directions. The reference data can be a number, a marker of the measurement point or in the case of positional measurements a terrestrial aiming point. When measuring angular characteristics, i.e. the interdependence of angles and external forces or moments, the latter are considered as references. For the measurement of contours the distance has to be fed in or read in, or computed by accelerometers within an integrated inertial system, respectively. By such a system and through the application of the invention the measurement accuracy of movements and gravity anomalies can be increased while refraining from external references otherwise necessary under the present state of the art.

Claims

1. A method for measuring spatial angles at at least two different measurement positions by means of an apparatus including three gyros comprising the steps of:

moving said apparatus in a first predetermined order to each of said measurement positions in order to make measurements with respect to predetermined reference directions at said measurement positions, said gyros continuously outputting gyro signals;

continuously registering said gyro signals;

registering reference data at each of said measurement positions, said reference data having a predetermined relationship with said measurement positions at which said spatial angles are to be determined;

registering a first time t at which said reference data are registered;

moving said apparatus in a second predetermined order opposite to said first predetermined order and registering reference data and registering a second time t at which said reference data are registered for each of said measurement positions;

calculating for each of two corresponding reference data, a difference of said first registered time t and said second registered time t at which the reference data are registered, and a difference of said registered gyro signals at which the reference data are registered, said registered time difference and said registered gyro signals difference being used as input for a measurement equation for optimally estimating a system error time function;

optimally estimating said system error time function using said measurement equation; and

correcting said registered gyro signals by means of said estimated system error time function, thereby producing measurements of said spatial angles at said measurement positions.

2. The method of claim 1, wherein said measurement equation includes first and second models for the development with time of the estimated system error time function,

said first and second models including sensor errors,

said first model being computed forward in time for a time 0 at the beginning of the measurement,

said second model being computed backward in time for a time T at the end of the measurement,

said first and second models being set equal to measurement differences y_j in order to form a measurement equation comprising:

space="preserve" listing-type="equation">y.sub.j,v =H·

(Φ

(t.sub.j2,

     0)-Φ

(t.sub.j1,

     0))·

x.sub.0 +v.sub.j

space="preserve" listing-type="equation">y.sub.j,r =H·

(Φ

(t.sub.j2, T)-Φ

(t.sub.j1, T))·

x.sub.T +v.sub.j

wherein

j indicates a direction of measurement

₁ indicates a first point in time

₂ indicates a second point in time

_v indicates calculation forward in time

_r indicates calculation backward in time

H=(I 0

     0)=measurement matrix

Φ

(t,

     0)=transition matrix of point of time 0 to T

x=(.sub.ε

T _d T _r T)T=system error vector

ε

=angle error vector

d=gyro drift vector

r=vector of time dependent gyro drift variation

v=measurement noise vector

said angle error vector ε

, said gyro drift vector d, said vector of time dependent gyro drift variation r, and said measurement noise vector v being taken for optimally estimating said system error vector x,

wherein two time functions of the optimally estimated system error vectors, x_v and x_r are computed based on the beginning and the end of the measurements as a foundation for a joint time function x obtained through formation of a weighed means value computation,

said correction of said registered gyro signals being carried out by means of said system error time function.

3. The method of claim 1 wherein repeated measurements with corresponding reference data are carried out so that the arithmetic mean (t_j2 +t_j1) between the measurement times t_j2 and t_j1 at corresponding reference data positions does not remain constant,

said repeated measurements with corresponding reference data being carried out for the purpose of observing a time dependent gyro error.

4. In the method of claim 1, said apparatus further including a carrier upon which said three gyros are mounted, and a track having a trajectory,

said step of moving said apparatus comprising moving said carrier along said track to each of said measurement positions,

said method further comprising the step of measuring the distance of each location with respect to a starting location, said distances being taken as reference data,

said steps of moving said carrier along said track and measuring the distance of each location with respect to a starting location being operative for measuring a trajectory of said apparatus.

5. The method of claim 4 further comprising the step of measuring the relative direction between said track and said carrier at each measurement position.

6. In the method of claim 1, said apparatus further including a carrier having an inertial navigation system, and three accelerometers,

said method further comprising the step of computing a system error vector using the equation comprising:

space="preserve" listing-type="equation">x=(.sub.ε

T .sub.δ

Vn T .sub.δ

Sn T .sub.d T .sub.r T .sub.b T)T

wherein

x=system error vector

ε

=angle error vector

T=time at the end of a backward in time measurement

δ

Vn=velocity error vector,

δ

Sn=position error vector,

b=vector of the acceleration measurement error,

d=gyro drift vector, and

r=vector of time dependent gyro drift variation.

7. The method of claim 6, wherein said measurement equation includes first and second models for the development with time of the estimated system error time function,

said first and second models including sensor errors,

said first model being computed forward in time for a time 0 at a beginning of the measurement,

said second model being computed backward in time for a time T at the end of the measurement,

said first and second models being set equal to measurement differences y_j to form a measurement equation comprising:

space="preserve" listing-type="equation">y.sub.j,v =H·

(Φ

(t.sub.j2,

     0)-Φ

(t.sub.j1,

     0))·

x.sub.0 +v.sub.j

space="preserve" listing-type="equation">y.sub.j,r =H·

(Φ

(t.sub.j2, T)-Φ

(t.sub.j1, T))·

x.sub.T +v.sub.j

wherein

j indicates a direction of measurement

₁ indicates a first point in time

₂ indicates a second point in time

_v indicates calculation forward in time

_r indicates calculation backward in time

H=(I 0

     0)=measurement matrix

Φ

(t,

     0)=transition matrix of point of time 0 to T

x=(.sub.ε

T _d T _r T)T=system error vector

ε

=angle error vector

d=gyro drift vector

r=vector of time dependent gyro drift variation

v=measurement noise vector

said angle error vector ε

, said gyro drift vector d, said vector of time dependent gyro drift variation r, and said measurement noise vector v being taken for optimally estimating said system error vector x,

wherein two time functions of the optimally estimated system error vector, x_v and x_r are computed based on the beginning and the end of the measurements as a foundation for a joint time function x obtained through formation of a weighed means value computation,

said correction of said registered gyro signals being carried out by means of said system error time function.

8. In the method of claim 6, said step of taking said position measurements further including the step of taking velocity measurements, said system error time function being calculated using the measurement matrix comprising:

space="preserve" listing-type="equation">H=(0 I I 0 0

     0).

9. In the method of claim 6, said step of taking said position measurements further including the step of taking angular measurement with respect to identical reference directions, said system error time function being computed using the measurement matrix comprising:

space="preserve" listing-type="equation">H=(I 0 I 0 0

     0).