Sighting and navigation system

 

(57) Abstract:

The invention relates to aircraft instrumentation and can be used as part of the on-Board aircraft equipment, ensuring the fulfilment of the tasks of navigation and target acquisition. The proposed complex contains inertial-satellite system associated with the target designation system. Added block difference, the delay block, the block allocation errors, the set of parametric functions and block optimal information processing. These units compensate for errors in the determination of the navigation parameters of the aircraft and targeting parameters. The invention provides improved precision of complex operation and, consequently, the performance of the combat effectiveness of the aircraft, equipped with the proposed complex. 1 Il.

The invention relates to the field of aviation instrument, in particular to the on-Board equipment, ensuring the aircraft navigation and targeting of a specified goal.

Known analogues, see, for example, in the book [1] edited by Kharisov C. A. , Perov, A. I., Boldin Century A. "global satellite navigation system GLONASS, Moscow, IPGR, 1998; in the book [2] Baleada sighting and navigation system, described in [2], pp. 476-491. This complex contains consistently United inertial-satellite (interconnected satellite navigation and inertial navigation system [2], page 485) and target designation system (radar or optical radar station [2], page 485).

In the inertial-satellite system corrects madelinemadeline inertial data and the suppression of high-frequency noise data from navigation satellites. Based on the angles of the aircraft evolutions and own measurements (range to target, the viewing angles of the target) in the target designation system formed the coordinates of the target. When exposed specialoperating interference in the ranging channel targeting system can be a considerable increase in the bias range (tilt range) and when working from navigation satellites GPS mode unauthorized access ([1], page 256) systematic error on the coordinates can be up to 200 m ([1], page 264).

The objective of the invention is to improve the accuracy of operation of the complex.

The technical result is achieved by the fact that in sighting and navigation system that contains p is POC formation of parametric functions and connected between the first output of the targeting system and the entrance of inertial-satellite system, connected in series block difference, the delay block, the block allocation errors, block optimal information processing, the second output of which is connected to the second input of the targeting system, the second output of which is connected to the second input of the delay unit, the second output of which is connected to the input of the processing unit of parametric functions, the output of which is connected to the second input of the block allocation errors, and to the second input of the differential is connected to the second output of the inertial-satellite system.

The drawing shows a block diagram of the proposed complex, which contains:

1 - inertial-satellite system ASCS; 2 - target designation system of SCU, 3 - unit optimal information processing BOOI, 4 - block differences BR, 5 - block formation of parametric functions BFPF, 6 - block allocation errors BVP, 7 - delay block, BRS.

Communication between blocks is performed, for example, in the standard sequential code.

Examples perform standard arithmetic device (4 BR, BFPF 5, BVP 6, FP 7), performing the operations of sum, difference, multiplication, division, for the tion of the machine", Moscow, Higher school, 1981, page 16.

The system works as follows.

ASC 1 measures the geographic location coordinates of the plane A1, A2, A3(with errors X1X2X3close to systematic), which, as noted above, in the sequential code with the second output ISS 1 serves to the second input of BR 4, and the angles of the aircraft evolutions course A4roll A5the pitch of A6(with errors X4X5X6close to systematic), which from the first output ISS 1 served on the first input SCU 2, measuring the range to the target A7and angles of sight targets A8, A9(accordingly with the errors, where X7X8X9- systematic error, fluctuation error type white noise). In SCU 2 in accordance with the measured and the received parameters are generated target coordinates relative to the plane of its axis ([2], page 227)

S1=A7cosA8cosA9, S2=A7sinA8cosA9, S3=A7sinA9< / BR>
and the geographical coordinates of the target relative to the plane

A1TS=S1cosA6sinA4-S2(cosA5sinA6cosA4-sinA5sinA4)+S(cosA5cosA4sinA6+sinA5cosA4+S3(cosA4cosA5-sinA5sinA6sinA4)

ATRUDGED 3TS=S1sinA6+S2cosA5cosA6- S3sinA5cosA6.

The signals S1, S2, S3, sinA4, cosA4, sinA5, cosA5, sinA6, cosA6, A7, sinA8, cosA8, sinA9, cosA9from the second output SCU 2 go to the second input of BR 7.

Signals A1TS, AC, ATRUDGED 3TSfrom the first output SCU 2 are received at the first input 4 BR. When known, introduced in BR 4 as a reference signal before the flight (or flight), the geographical coordinates of the detected target A10, A20, A30in BR 4 on the standard arithmetic operations of summation and difference signals are formed for i = 1, 2, 3

< / BR>
where the partial derivatives of ([4], Bodner Century A. "Devices primary information", Moscow, Mashinostroenie, 1981, page 102)

< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
< / BR>
For random processes like white noise with variance Cto2will be

then

< / BR>
this output signal 4 BR arrives at the first the time

< / BR>
< / BR>
or in General

< / BR>
thus = 0 for i = 1, 2, 3; = 1when i = 4, 5, 6, =2when i = 7, 8, 9;

a11=a22=a33=a41=a52=a63= a71=a82=a93=1;

a12= a13= a21=a23=a31=a32= a42=a43=a51=a53=and61=a62=a72=a73=a81=a83=a91= a92=0:

Signal bi(t) from the first output BZ 7 is supplied to the first input of BVP 6.

Formed in BRS 7 signals

< / BR>
from the second output BZ 7 is fed to the input BFPF 5, which is the standard arithmetic device, in which the received signals by multiplying, summing, difference generated parametric functions

a14(t)-a19(t-),

a24(t)-a29(t),...,

a94(t)-a99(t-),

F2i(t-)

which output BFPF 5 proceed to the second input of BVP 6, which is the standard arithmetic device, in which the operations of multiplication, summation, difference, division signals are formed errors and fto< / BR>
< / BR>
,

where ([5] , Bronstein, I. N., Semendjajew K. A. "Handbook of mathematics", Moscow, Nauka, 1983, pages 157-163, [6] Kuzovkov N. So, Sa is the system

< / BR>
Here the sign (-1)Z)is determined by the number Z() inversions lookup

< / BR>
the sum of 9! components, which are the works of the nine factors each containing one element from each row and one element from each column, and

< / BR>
(here instead of a11, ... , a91substituted b1, ... , b9), ... ,

< / BR>
(here instead of a19, ... , a99substituted b1, ... , b9)

< / BR>
(here instead of a11, ... , a91populated with F12, ... , F92)

< / BR>
(here instead of a19, ... , a99substituted F12, ... , F92).

Signals fto(K=1, ... , 9) output BVP 6 fed to the input of BOOI 3, containing nine of the optimal filter ([7] sage E., Mels D. "Theory of estimation and its application in communications and management." Moscow, Communication, 1976, pages 287-289) for each signal xkoperations are performed:

- integration of fto(t)dt

- division

- the difference

- multiplication

- integration

where optimal error estimates for the background noise with variance f-to1.

For example, if fto=1=const dispersion error

Dxto=to= (t+aoHK--->0.

The mathematical expectation of systematic components

< / BR>
when

nto= (t+ao)-1,

which implies that, over time, i.e., best estimate tends to the actual value of the systematic error of Xto.

From the first output BOOI 3 signals estimated systematic errors of location coordinates and angles evolutions of the aircraft arrives at the entrance of ASCS 1.

From the second output BOOI 3 signals estimates of the systematic components of the distance to a chain and angles of sight targets, proceed to the second input of SCU 2, in which the correction parameters when K=7, 8, 9.

< / BR>
where over time (t+To)-10, i.e., correction is carried out with precision fluctuation components of the error.

In ISS 1 on received signals (K=1-6) are correction parameters

< / BR>
which implies that over time i.e. the adjusted parameter values tend to the actual values of Atothat testifies to the achievement of the technical result.

The system outputs are the first and second outputs ISS 1, SCO 2, the signals from which oomplex, contains one United inertial-satellite system and the target designation system, characterized in that it additionally introduced the set of parametric functions and connected between the first output of the targeting system and the entrance of inertial-satellite system, connected in series block difference, the delay block, the block allocation errors and block optimal information processing, the second output of which is connected to the second input of the targeting system, the second output of which is connected to the second input of the delay unit, the second output of which is connected to the input of the processing unit of parametric functions, the output of which is connected to the second input of the block allocation errors and to the second input of the differential is connected to the second input of the inertial-satellite system.

 

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