RU2726582C1 - Device for assessing possibility of launching soyuz-2 space rocket based on weather survey results - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: invention relates to rocket engineering. Device for evaluating the possibility of launching Soyuz-2 space rocket according to the results of meteoric survey has a unit for constructing a program trajectory of output and analysis of calculation results, the outputs of which are connected to a unit for indicating the possibility of launching. Device also has an information receiving unit for receiving weather survey data and an arithmetic logic unit whose inputs are connected to the outputs of the information receiving unit.EFFECT: reduced time of wind characteristics calculation.1 cl, 1 dwg

Description

The proposed invention relates to the field of rocketry, in particular to on-board devices for evaluating the possibility of launching a space rocket (ILV) "Soyuz-2" based on the results of meteorological sounding.

The relevance of this invention is determined by the need for prompt and independent decision-making on the launch of the carrier rocket, using the actual parameters of the atmosphere, determined as a result of sounding immediately before the launch of the ILV.

Background of the invention:

Consideration of approaches to solving the problem of determining the possibility of launching an ILV based on the actual parameters of the atmosphere should begin with devices already used in rocket technology, alternative to the use of devices for determining the possibility of launching taking into account atmospheric parameters.

At present, an external device is known based on the creation of an analogue of the ILV control system (CS), located directly at the Soyuz-2 ILV control system manufacturer in Yekaterinburg. The actual parameters of the atmosphere are transferred there, entered as initial data into an analogue of the control system, the parameters of the launch trajectory are calculated and compared with the tolerances. Based on the results of this comparison, a conclusion is made about the possibility of launching an ILV. This approach has a number of disadvantages, namely: the remoteness of the device, which requires stable and reliable communication channels; dependence on the performance of the manufacturer; the duration of the launch decision; availability of an analogue of an expensive SU.

In the proposed device, due to a slight modification of the ILV control system directly at the launch complex, in the shortest possible time before launch, using the meteorological data, the parameters of the launch trajectory are calculated, they are compared with tolerances and the result is given about the possibility of launching.

Meteorological data are determined by a representative of the meteorological department immediately before launch in the form: wind speed in meters per second and wind azimuth in degrees, depending on the altitude in the range from 0 km to 20 km with a step of 1 km. Precision of representation - whole numbers.

To assess the admissibility of wind effects on the launch vehicle, the modules of the projection differences on the 0Y1 and 0Z1 axes of the associated coordinate system of the actual wind speeds are calculated based on the data from atmospheric sounding and wind speeds taken into account when calculating the onboard flight task. The corresponding gradients of these differences are also calculated.

Data on the systematic wind speeds taken into account when calculating the on-board flight task are contained in the memory and represent the values of the mathematical expectations of the speed of the zonal speed of the meridional wind in the area of the cosmodrome in accordance with OST 92-9704-95, and restrictions on the difference between the projections of the actual and accounted for when calculating the onboard flight assignment of wind speeds and gradients of changes in these differences in height.

The modules of the differences between the projections on the lateral ILV axes of the actual wind speed and the wind speed taken into account when calculating the on-board flight task should not exceed the values of the restrictions on the values of the differences between the projections of the actual and taken into account when calculating the on-board flight task of wind speeds and the gradients of these differences in height stored in the storage device.

For a layer thickness of 1 km, the moduli of the gradients of the change in height of the differences in the projections of the velocities should not exceed the values of the gradients of the change in the differences of the projections of the actual and taken into account when calculating the onboard flight task of wind speeds.

Differences between the projections of the actual wind and wind velocities on the ILV transverse axes, taken into account when calculating the onboard flight mission, are determined by the formulas

- разности проекций на оси OY1 и OZ1 связаннойWhere

- the difference between the projections on the axes OY1 and OZ1 of the connected

coordinate systems of the actual wind and wind speeds taken into account when calculating the onboard flight mission;

W _B = W _B (H) - actual wind speed;

A _B = A _B (Н) - azimuth of the direction from which the actual wind blows, counted clockwise from the direction to the North;

- скорость систематического зонального ветра, направленного с Запада на Восток, учитываемого при расчете бортового полетного задания;

- the speed of the systematic zonal wind directed from West to East, taken into account when calculating the onboard flight mission;

- скорость систематического меридионального ветра, направленного с Юга на Север, учитываемого при расчете бортового полетного задания;

- the speed of the systematic meridional wind directed from South to North, taken into account when calculating the onboard flight mission;

А _П - launch azimuth, counted clockwise from the direction to the North;

H - height;

ϕ = ϕ (Н) - programmed pitch angle;

ψ = ψ (Н) - programmed yaw angle.

In the formulas, the differences in the projections of the velocity on the “programmed” connected ILV axes are determined. The initial roll-off of the ILV, eliminated by the 22nd second of the flight, caused by the difference in the azimuth of the LV plane I at the moment of launch from the launch azimuth, and the corresponding distributions of control actions are taken into account by the LV CS.

Calculations by formulas are carried out for the nodal points H _i indicated in the weather report based on the results of atmospheric sounding.

определяются линейной интерполяцией.For Hi points, the values

determined by linear interpolation.

The values ϕ (Н) and ψ (Н) are taken in accordance with the calculated programmed flight path.

сравниваются с соответствующими ограничениями по разности скоростей, хранящимися в запоминающем устройстве, которые также приводятся к узловым точкам Hi линейной интерполяцией.The angles are set with an accuracy of 0.1 °, heights - 0.1 km, velocities - 0.1 m / s. Modules of quantities

are compared with the corresponding constraints on the difference in speed stored in the memory, which are also converted to the nodal points Hi by linear interpolation.

Gradients in height (GR (H _i )) the difference in the projection of speeds on the transverse axes OY1 and OZ1 are calculated by the formula

respectively along the axes OY1 and OZ1.

For H = 0, no gradients are defined.

сравниваются с соответствующими ограничениями по градиентам, хранящимися в ЗУ, которые приводятся к узловым точкам линейной интерполяцией.Modules of the resulting gradients

are compared with the corresponding gradient constraints stored in the memory, which are reduced to anchor points by linear interpolation.

When launching ILV as part of some RCS, requirements may be imposed on wind characteristics according to the generalized criterion K _y , determined by the expression

ΔН = H _i -H _i-1 ,

where, M _w , M _gr - speed and gradient scaling divisors.

The check is carried out for axes OY1 and OZ1.

Requirements for assessing wind acceptability according to the generalized criterion for specific RSC, the ranges of control heights by the generalized criterion Kу and the values of the scaling divisors M _w , M _gr are stored in the memory and are selected depending on the RSC.

In case of a positive result of checking the calculation of the wind field and its compliance with all acceptance criteria, the device gives a positive indication of the possibility of launching, taking into account the actual weathering data.

If the conditions for the admissibility of wind characteristics are not met, the onboard flight task is calculated, which consists in building a programmed launch trajectory and analyzing the calculation results with the quantitative requirements for calculating the onboard PZ.

According to the results of the calculation, if these monitored requirements are within the controlled tolerances, then the device gives a positive indication of the possibility of launching, taking into account the actual weathering data. If these requirements are outside the tolerance limits, then the device gives a negative indication of the possibility of starting.

This approach, in terms of its accuracy characteristics, corresponds to the standard definition of the permissible wind field, but significantly exceeds it in terms of the speed of making a decision on the possibility of launching and excludes dependence on third-party organizations.

The financial cost of manufacturing the device is negligible. The objective of the invention is to develop a device for evaluating the possibility of launching a space rocket "Soyuz-2" according to the results of weathering.

A device for evaluating the possibility of launching a space rocket "Soyuz-2" according to the results of meteorological sounding (block 1), equipped with an information receiving unit (BPI) (block 2), the outputs of which are connected to an arithmetic logic device (ALU) (block 3), is declared, the outputs of which are connected to the block for constructing the programmed trajectory of the injection and analysis of the calculation results (block 4), the outputs of which are connected to the indication block about the possibility of launching (block 5), is shown in FIG. 1.

A digital signal processor can act as an arithmetic logic unit (ALU). A read-only memory with a capacity of up to 4 GB can be used as an information receiving unit (BPI). As a block for constructing a programmed launch trajectory and analyzing the calculation results, both a standard onboard computer installed on board the ILV and a separate independent digital computer complex can be used. Any light and sound signaling device can act as an indication unit about the possibility of launching.

The technical result of the invention is the ability to promptly make a decision on the launch of the carrier rocket, based on the actual parameters of the atmosphere, determined as a result of meteorological sounding immediately before the launch of the ILV, regardless of third-party organizations, with the condition of minimal revision of the control system of the LV and, as a consequence, reducing the time spent on calculating the permissible wind turbines. characteristics and increasing the possibility of successfully accomplishing ILV tasks.

The required technical result is achieved by the fact that in a single device the acquisition of actual weathering data is combined with the subsequent calculation of the permissible wind characteristics and the possibility of an independent analysis of the controlled trajectory parameters, the fulfillment of the main launch task and the issuance of an indication of the launch vehicle's readiness for launch.

Thus, the positive effect of installing this device is:

- reduction of time spent on calculation of permissible wind characteristics;

- independence of the calculation from third-party organizations;

- in the low cost of the proposed invention;

- the promptness of making a decision on the possibility of launching when the launch is postponed to the reserve launch date, with launch delays.

SOURCES OF INFORMATION

1. OST 92-9704-95. Mathematical expectations of the zonal wind speed.

2. Ed. IN AND. Varfolomeeva and M.I. Kopytov. Design and testing of ballistic missiles / - M .: Oborongiz, 1970. - 392 p., Ill.

3. N.I. Panichkin, Yu.V. Slekushkin, V.P. Shinkin, N.A. Yatsinin. Design and design of spacecraft: Textbook for secondary educational institutions / - M .: Mechanical Engineering, 1986. - 344 p., Ill.

4. Pencak I.P. Flight theory and ballistic missile design: A textbook for technical schools. - M .: Mechanical Engineering, 1974 .-- 344 p., Ill.

Claims (1)

A device for evaluating the possibility of launching a space rocket "Soyuz-2" based on the results of meteorological sounding, equipped with a block for constructing a programmed trajectory of launching and analyzing the results of calculation (BPPTVARR), the outputs of which are connected to an indication unit about the possibility of launching, which differs from the known ones in that it contains the block information reception (BPI) for receiving weather sounding data and an arithmetic logic unit (ALU), the inputs of which are connected to the BPI outputs, which together provide actual meteorological data to the BPPTVARR unit, based on the calculation results of which an operational decision is made about the possibility of launching.

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