RU22705U1 - "ELECTRONIC" ROCKET AIMING DEVICE - Google Patents

Abstract

An electronic missile aiming device containing a ground digital computer (NTSVM), a control device and command-gyroscopic devices (GGP), characterized in that in order to simplify the design and reduce the time to determine the angle of turn of the GGP into the target plane with the required accuracy, from The gyrocompass was brought out of its composition, the role of which is assigned to the simulation block introduced into the NTSVM, and connected to the unit for calculating the required angle of the KGP solution, which makes it possible due to the speed of the NTSVM met statistical test house according to the dependence δ = (β + μ), where angle β is a random variable modeled according to a given distribution law; angle μ is a discrete value with an increment set at each step of the simulation, the initial value of which is zero, calculate the angle of the GGP turnaround with the required confidence probability that a missile enters the chain.

Description

ROCKET ELECTRONIC AIMING DEVICE

The device relates to the field of missile guidance and can be used to aim the missiles of a tactical missile being upgraded in a horizontal plane by using simulation data obtained in the process of "electronic launches at a given range."

There is a method of aiming 1, which consists in measuring the orientation direction on the ground, converting it and transmitting it to the on-board equipment of the control system (BASU) of the rocket for the purpose of displaying command-gyroscopic devices (GGP) in the launch plane. It requires significant time costs, in particular, in the preparation and conduct of a launch from an unprepared starting position. In addition, in its technical implementation, expensive equipment is used (gyrocompass, milestones), which will practically not be needed in case of modernization of the aiming system (SPR).

The purpose of the utility model is to simplify the design of the aiming system and reduce the time for preparing and delivering missile strikes from an unprepared launch position, which is achieved by eliminating the gyrocompass and milestones from the SPr.

The essence of the "electronic aiming" method is illustrated by the circuit shown in FIG. 1. It includes a number of stages that provide a solution to the most important practical problem.

1. The rationale for the initial data for aiming missiles.

1.1. The coordinates of the launch point hta, uta are determined by the topographic reference system (STP) of the self-propelled launcher (SPU) or in another way; the coordinates of the target xs, uz are indicated in the combat order for the preparation and launch of a missile strike.

inverse geodesic problem and is considered a given value.

1.3. The angle of arrival of SPU az at the launch point is within ac ± L, where A is the marginal error of arrival (the value is discrete and constant for this STP).

2. The calculation of the directional angle of the CGP act is carried out using the dependency

"Kga Ots + p + q Ots + 5, (1)

where 8 (P + M-) is the angle of the CGP to the launch plane; the angle P is a random value,, the angle jj, is a discrete value, the initial value of which is zero, and then at each step of the simulation it is given a specific increment.

3. The draw of the angle P is made according to the uniform distribution law due to the simplicity of its imitation. It is known 2 that the modeling dependence has the form

where b + A, a -A; Је ОД.

4. The calculation of the angle of the act is carried out according to the formula (1), which is taken as the basis for the production of “electronic launches (calculation of rocket flight paths). The required number of the latter is found according to expression 3

p (i-p)

„(± 0), (3)

where s is a constant value (e 0.01; 0.05); Q is the confidence level specified by the tabular data.

The coordinates of the KhTSIuts obtained during the "electronic launches with

taking into account each drawing of the angle P and setting the increment step of the angle c., are determined using the relations

x1z VTs-8sh (a3 + p-ts), Uts VTs-ss8- (a3 + p + q).

P (b-a) Ј + a, (2)

Confidence Levels and Laplace Functions

Table

Claims (1)

An electronic missile aiming device containing a ground digital computer (NTSVM), a control device and command-gyroscopic devices (GGP), characterized in that in order to simplify the design and reduce the time to determine the angle of turn of the GGP into the target plane with the required accuracy, from The gyrocompass was brought out of its composition, the role of which is assigned to the simulation unit introduced into the NTSVM, and connected to the unit for calculating the required angle of the KGP solution, which makes it possible due to the speed of the NTSVM met House of statistical tests based on
δ = (β + μ),
where angle β is a random variable modeled according to a given distribution law;
the angle μ is a discrete value with an increment set at each step of the simulation, the initial value of which is zero,
calculate the angle of rotation of the QGP with the required confidence probability, which ensures that the missile enters the chain.