DE2912586C1 - Procedure for calculating the reserve for the defense weapons of an air defense system - Google Patents

Description

The invention relates to a method for calculating the reserve for the defensive weapons of a Air defense system according to the preamble of claim 1. Such a method is based on the State of the art.

In a fire control system for air defense systems, the lead computer is of particular importance. The problem with the lead calculation is to aim the weapon so that the target and projectile meet at the same time in the same place. As shown in FIG. 1 to explain the calculation of the point of impact vector, in order to determine this point of impact vector r _{T, in} addition to the target data supplied by a sensor, the projectile trajectory, which is dependent on the ballistics of the projectile, must be taken into account. The following two equations can be set up to calculate the lead:

l-TT = T _u + V _ZiEL -T _f (1)

2- Tf = f _bed (r _T ) or 7 _T = fö _u (T _f ) (2)

In equation 1, 7 _M = measuring point ^{vector, v} ziEL = target speed, 2} = projectile flight time (unknown).

Equation 2 represents an empirically determined, non-algebraic function. The resolution of the System of equations (1) and (2) can therefore mathematically only be carried out by an iteration calculation.

Analog or digital computers can be used in the lead calculator to solve the systems of equations I and 2. When using an analog computer, a comparison circuit with a servo system is generally used. A wave from the computer simulates the projectile flight time. A signal, which is obtained from the difference between the point of impact vectors according to equations 1 and 2, drives the shaft until the correct projectile flight time is determined.
When using a digital computer, the

κι solution usually according to the iteration process.

One difficulty here, however, is the short computing time required, which is due to the necessity of the Real-time operation arises.

The invention is based on the object of making it possible for a fire control device of the type mentioned at the outset to be able to determine the lead according to a modified iteration method with considerably reduced computing time.
According to the invention, this object is achieved with the features according to the characterizing part of claim 1.

Of the values of the possible projectile flight time given in parallel arithmetic operations, the one that is most obvious to the true projectile flight time is considered to be that which is derived from the difference between the results from the two equations of the system of equations and the difference values. supplies the smallest value to the other arithmetic operations. In the following, an equation (3) from η equation systems (1), (2) is given to determine the projectile flight time and the difference Ar of the two results of each equation system is formed.

^r T \\ ^{= r} M + ^V Zial'Tfi

^r T2 \ ⁼ fb ~ ll

^r T \ n ^{= r} M ~ t ~ VZiel '

^r T2n ⁼ fb ~ all (Tf ")

-Tr ₂₀ ) = Ar ₁

= Ar ₁

-Tr ₂₁ ) = Ar _n

Of the η by simultaneous calculations results obtained η Ar ₁ is the smallest value determined Ar ₁ min. The hit point vector r _Ti calculated with the projectile flight time T _fi , which led to the result Ar ₁ min, is used to determine the lead.

In order to keep the number of necessary parallel computing stages as small as possible, according to an advantageous development of the invention, an approximate value for the projectile flight time is determined from the target data 7 _M and T _{M, which is used to obtain the}

required different projectile flight times for the parallel computing stages is varied by an additive value ± mAt.

The value At should be chosen so that At = 2 ε, where ε is the reasonable error

is designated above the true projectile flight time and

m the values m = 0,1,2

1! Assumes.

Further details of the invention are given with reference to FIGS. 2 explained in more detail.

In Fi g. 2 shows a block diagram of a fire control computer. The flying object position data 7 _M and, supplied by a sensor (not shown)

r _M arrive in parallel at a stage 1 for coordinate transformation and for speed and acceleration calculation, to a stage 2 for the approximate determination of the projectile flight time 7} "and to the input of a number of η arithmetic units Dl, Dl ... Dn. The lead and ballistic arithmetic operations are carried out in the arithmetic units. The processing units are also connected to the output of stage 1 on the input side. The approximately determined projectile flight time from stage 2 is fed to a further input of the arithmetic unit Dl. Correspondingly, the arithmetic units Dl ... Dn receive a varied projectile flight time (Tp ± 1.2, .. JtAt) via an addition stage AsI, AsI ... Asn.

Difference values ArI, ArI . A switch S controlled by stage 3 is used to select the output value of that arithmetic unit Dl, Dl ... Dn for the final calculation of the gun angle which led to the formation of the smallest differential value Ar . The signals required for the alignment of the weapon are generated in stage 4.
The working according to the selection principle

K) for the calculation of the lead, as described above, requires considerably less computing time than the iteration method. The parallel, similar structure of the computing units Dl, Dl ... Dn also gives a fire control computer, which works according to the principle described, inherent redundancy, that is, the failure of one or more of the η digital computers only reduces the computational accuracy in the worst case.

For this purpose 2 sheets of drawings

- blank page -

Claims (2)

Patent claims: 1. Method for calculating the reserve for the anti-aircraft weapons of an anti-aircraft system from the projectile flight time with a digital computer using an equation system solvable by iteration calculation for the determination of the point of impact, which takes into account the target data continuously obtained from the echo signals of a follow-up radar and the ballistics of the projectile characterized in that the equation system (I ₅ 2) in a parallel process with different values of the independent variable projectile flight time (T _F ) by simultaneous arithmetic operations in several (n) independent arithmetic units (Z) I, D2.:.Dn), consisting of A lead and ballistics part or program part each is solved, the projectile flight time (Tp) which delivers the lowest value as a result when the system of equations is solved at the same time and the difference is subsequently calculated, being used for the lead determination. 2. Fire control device according to claim 1, characterized in that an approximate value for the projectile flight time (Tf ₀ ) is determined for the execution of the arithmetic operations taking place at the same time from the target data, which is varied by an additive value ± mA t , the value At = 2ε is chosen; where m = 0.1.2 ... (j - 1) and ε = reasonable error between the true projectile flight time and the projectile flight time Tf ₁ determined using this method.