US5485384A — On-board navigation system for an aerial craft in…

Claim 1

Independent Claim 304 words

An on-board navigation system for an aerial vehicle of the type including an inertial navigation facility (10) delivering an estimation of the position and velocity of the vehicle with respect to the terrestrial surface, a SAR synthetic aperture sideways looking radar (12) producing a SAR radar image of the territory in the vicinity of the point (Mo) overflown by the vehicle, memory means (16) containing a reference map of the territory overflow, means (17) for comparison based on alignment of said SAP, radar image produced in flight with the stored reference map and providing an alignment deviation δ in two perpendicular directions and computing means (18) linked to the memory means (16), to the inertial navigation facility (10) and to the means of comparison (17), which include filter means of the KALMAN type, and which deliver an inceptor to the KALMAN filter for the estimation of the inertial errors in position and in velocity as a function of the alignment deviation δ, wherein said computing means (18) express the alignment deviation as a function of the estimation error vector ΔU associated with the state vector U consisting of the components of the vectors P, V for the position and relative velocity of the vehicle, in accordance with the following equation: ##EQU25## in which: η is the vector of alignment error in two perpendicular directions ηx, ηy; ΔX and ΔY represent the inertial error in position of the vehicle in two horizontal perpendicular directions; ΔZ represents the inertial error in altitude of the vehicle; ΔV represents the vector of inertial errors in velocity of the vehicle; and f(ΔZ, ΔV) and g(ΔZ, ΔV) are two scalar functions; and wherein the filter is a KALMAN-BUCY filter with gain matrix K such that the estimate Δ U of the vector of estimation error is equal to Δ U=K.δ.

Claim 2

Dependent Claim 304 words

An on-board navigation system for an aerial vehicle of the type including an inertial navigation facility (10) delivering an estimation of the position and velocity of the vehicle with respect to the terrestrial surface, a SAR synthetic aperture sideways looking radar (12) producing a SAR radar image of the territory in the vicinity of the point (Mo) overflown by the vehicle, memory means (16) containing a reference map of the territory overflow, means (17) for comparison based on alignment of said SAP, radar image produced in flight with the stored reference map and providing an alignment deviation δ in two perpendicular directions and computing means (18) linked to the memory means (16), to the inertial navigation facility (10) and to the means of comparison (17), which include filter means of the KALMAN type, and which deliver an inceptor to the KALMAN filter for the estimation of the inertial errors in position and in velocity as a function of the alignment deviation δ, wherein said computing means (18) express the alignment deviation as a function of the estimation error vector ΔU associated with the state vector U consisting of the components of the vectors P, V for the position and relative velocity of the vehicle, in accordance with the following equation: ##EQU25## in which: η is the vector of alignment error in two perpendicular directions ηx, ηy; ΔX and ΔY represent the inertial error in position of the vehicle in two horizontal perpendicular directions; ΔZ represents the inertial error in altitude of the vehicle; ΔV represents the vector of inertial errors in velocity of the vehicle; and f(ΔZ, ΔV) and g(ΔZ, ΔV) are two scalar functions; and wherein the filter is a KALMAN-BUCY filter with gain matrix K such that the estimate Δ U of the vector of estimation error is equal to Δ U=K.δ.

Claim 3

Dependent Claim 139 words

The system as claimed in claim 1, wherein said scalar functions f(ΔZ, ΔV) and g(ΔZ, ΔV) have an observed alignment deviation in accordance with the following equation: ##EQU26## having the following observation matrix ##EQU27## in which the terms α1, β1, A and B depend only on the kinematics and the estimated trajectory and on the estimated coordinates of the sighted point on the ground, and wherein the gain matrix of the KALMAN-BUCY filter equals K=Σ.sub.U.sup.-.H.sup.t.(H.Σ.sub.U.sup.-.H.sup.t +Ση).sup.-1 where E U - denotes the covariance matrix of the vector of estimation errors before adjustment, Ση denotes the covariance matrix of the alignment error vector, and wherein a post-adjustment residual estimation error ΔU + is determined according to the formula: ΔU.sup.+ =ΔU.sup.- -Δ U and having the following covariance matrix Σ U + : Σ.sub.U.sup.+ =(I-K.H).Σ.sub.U.sup.- where I denotes the identity matrix.

Claim 4

Dependent Claim 181 words

The system as claimed in claim 1, wherein said scalar functions f(ΔZ, ΔV) and g(ΔZ, ΔV) have an observed alignment deviation in accordance with the following equation: ##EQU28## having the following observation matrix ##EQU29## the terms αi, βi, A and B depending on the kinematics of the estimated trajectory and on the estimate coordinates of the sighted point on the ground, and wherein a first estimate .sub.Δ U of the vector of estimation errors is equal to: ##EQU30## with δ.sub.ΔZ 2 denoting the variance of the inertial error in altitude ΔZ before adjustment and with K1 which represents a first gain matrix of the KALMAN-BUCY filter and which is equal to: K.sub.1 =Σ.sub.U.sup.-.H.sup.t.(H.Σ.sub.U.sup.-.H.sup.t +Ση+Σ.sub.z).sup.-1 Σ U - denoting the covariance matrix of the vector of estimation errors before adjustment, Ση denoting the covariance matrix of the alignment error vector, and Σ z is a matrix which is equal to: ##EQU31## and a first residual estimation error dU being determined according to the formula dU=ΔU-.sub.Δ.spsb. .sub.U its covariance matrix Σ* u being equal to Σ*.sub.U =(I-K.sub.1.H).Σ.sub.U.sup.- with I denoting the identity matrix.

Claim 5

Dependent Claim 138 words

The system as claimed in claim 3, additionally comprising means for computing, from said first estimate .sub.ΔU of the vector of estimation error, a pseudo-measure δ* of the alignment deviation such that: ##EQU32## with .sub.ΔZ denoting the altitude component of said first estimate, and such that δ*≈H*.dU+η and having the following observation pseudo-matrix H* which is equal to ##EQU33## a second estimate d .sbsb.U of the vector of estimation errors is equal to .sub.d.sbsb.U =K.sub.2.δ* with K 2 denoting a second gain matrix of the KALMAN-BUCY filter and which is equal to K.sub.2 =Σ* .sub.U.H*.sup.t.(H*.Σ*.sub.U.H*.sup.t ÷Ση).sup.-1 and the means of adjustment determine a global estimation Δ U according to the formula Δ U=.sub.Δ.sbsb.U +.sub.d.sbsb.U the covariance matrix Σ U + of the residual error ΔU + after adjustment being defined by the formulae ΔU.sup.+ =ΔU-Δ U, Σ.sub.U.sup.+ =(I-K.sub.2.H*).Σ*.sub.U

Claim 6

Dependent Claim 60 words

The system as claimed in claim 3, wherein the covariance matrix Ση of the alignment error vector is equal to: ##EQU34## with δ a denoting the estimated standard deviation of the numerical noise of the alignment procedure, and δ h and δ z denoting respectively the estimated standard deviations of the horizontal and vertical location errors of the reference map.

Claim 7

Dependent Claim 206 words

The system as claimed in claim 2, wherein the terms αi, βi, and A and B are determined according to the following relations: ##EQU35## in which: ##EQU36## is the estimate of the relative velocity of the SAR antenna of the radar, the estimated coordinates of the phase center of which are: ##EQU37## V⊥ is the ortho-velocity equal to ##EQU38## R o =.sup.→ P .sbsb.s.sup.→ P .sbsb.M is the direction of sighting of the point M on the ground with coordinates ##EQU39## the values P s , V s , V⊥, P M , Ro being expressed in an orthonormal reference frame T=(O, X, Y, Z) defined at the estimated current point of the trajectory by: O: origin, point on the ground at the estimated vertical of the phase center of the SAR antenna; Z: upward vertical passing through the estimated position of the phase center of the SAR antenna; X and Y: in the horizontal plane beneath the craft, such that the estimated relative velocity .sup.→ V .sbsb.s of the antenna is contained in the plane (XOZ) and is directed towards the positive x axis, these values P s , V s , V⊥, P M , Ro being, in a reference frame, equal to: ##EQU40##

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1999-01-15	1999-07-17	2000-01-16	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	2003-01-15	2003-07-17	2004-01-16	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	2007-01-15	2007-07-17	2008-01-16	$7700.00	Window Closed / Lapsed

On-board navigation system for an aerial craft including a synthetic aperture sideways looking radar

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