RU2464526C1 - Method of minimising estrangement zone for multistage carrier rocket jettisonable parts - Google Patents

Abstract

FIELD: process engineering.

SUBSTANCE: proposed method consists in computing rocket jettisonable parts flight parameters before parts fall on earth during preflight action to define required estrangement zone from computed parameters. Elements differing in degree of collapse in dense atmosphere after detachment from carrier rocket are isolated in jettisonable parts. For these separate detachable elements, required estrangement zone are computed. After separation of jettisonable parts and during their independent flight till entry to dense atmosphere, generated is the signal to separation actuators to make then separate into aforesaid isolated elements.

EFFECT: decreased are of estrangement zones.

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Description

The invention relates to space technology, in particular to the development of minimizing exclusion zones for detachable parts of a multi-stage launch vehicle, taking into account the exclusion zones of spent parts of the launch vehicle allocated for its launches.

The issues of reducing the amount of environmental damage from falling parts separated from the carrier rocket (LV) during launches into orbits of spacecraft (SC) are becoming increasingly relevant in connection with the ever-expanding market for the provision of services for launching spacecraft into specified orbits. When developing new rocket and space complexes and cosmodromes, the task is to minimize exclusion zones allocated along the flight path. Existing methods for estimating and forecasting the necessary exclusion zones for spent boosters of LV stages show the need to allocate large areas on the earth's surface. There are different approaches to reducing these areas, for example, by controlled descent of the accelerator to predetermined areas due to on-board means located at the accelerator stage, through the use of parachutes, etc. (E.P. Kompaniets, A.D. Kuchma, A.M. Podolinny, Y.T. Shatrov. Investigation of ways to reduce the size of the falling areas of the separated parts of missiles. M., Mechanical Engineering, 1990).

From the patent literature there is a known method of minimizing exclusion zones for detachable parts of a multi-stage launch vehicle, which consists in the fact that at the stage of preflight preparation of a multi-stage launch vehicle, the motion parameters of the separated parts of the launch vehicle are calculated until they are lowered to the ground and the necessary exclusion zone (see, for example, RF patent No. 2086903, CL F42B 15/00, 1995).

One of the most important components that negatively affects the calculated and actually realized sizes of the accelerator fall fields is the multivariance of the nature of the destruction of the accelerator during an autonomous flight along the ballistic trajectory and the height at which it occurs, and, as a result, the need to take into account each of the options with its own aerodynamic and ballistic coefficients. And this is a significant drawback due to the need to take into account extreme combinations of options and highlight the maximum area areas.

The objective of the invention is to develop a method of minimizing exclusion zones for the detachable parts of a multi-stage launch vehicle to obtain a technical result in the form of simplifying flight preparation while minimizing the area of exclusion zones.

The problem is solved in that in the method of minimizing exclusion zones for the detachable parts of a multi-stage launch vehicle, the motion parameters of the detachable parts of the launch vehicle are calculated until they fall to the ground and the necessary exclusion zone, in accordance with the invention, is determined in the design of the detachable parts elements are distinguished that differ in the degree of their destruction in the dense layers of the atmosphere after separation from the launch vehicle; for these separately flying elements of the separated parts, they calculate The necessary alienation, and after separating the detachable parts from the launch vehicle during the autonomous flight of these parts on the trajectory until they enter the dense layers of the atmosphere, form a signal for the means of division and influence the design of the individual parts for their physical separation into selected elements.

The following shows an example of the proposed method, which is explained in more detail with the application of the figures, where Fig. 1 shows a diagram of the rocket stage accelerator, and Fig. 2 shows the calculated exclusion zones for the variant with the division of the spent accelerator, in accordance with the proposed method, and without it.

A way to minimize exclusion zones for the detachable parts of a multi-stage launch vehicle, for example, when launching into orbits by multi-stage launch vehicles, is that at the stage of preflight preparation and separation of a multi-stage launch vehicle, the motion parameters of the separated parts of the launch vehicle are calculated until they fall to the ground and according to the calculation results determine the necessary exclusion zone. In the design of the spent stage, elements are distinguished that differ in the degree of destruction in the dense layers of the atmosphere when separated from the LV, that is, elements that, in the case of their autonomous flight, will not be substantially destroyed in dense layers of the atmosphere (for example, propulsion systems), and elements that burn or partially burnt in dense layers of the atmosphere (for example, tanks, head fairings, instrument compartments). For these separately flying stage fragments, zones of necessary alienation are calculated. Means of dividing it into selected elements are introduced into the design of the launch vehicle, after which, during the autonomous flight of the spent stage in the trajectory, from the moment the stage accelerator is separated from the launch vehicle until it enters the dense atmosphere, they form a signal for the operation of the dividing means to the selected elements and affect the design of this accelerator in such a way as to carry out its physical division into selected elements, for example, by involving pyromedicines.

A signal for triggering the means for dividing the accelerator structure into elements can be implemented at a time instant calculated in advance for a given start-up and implemented using a timer.

Thus, in essence, the problem is solved by organizing a targeted division of the spent accelerator into fragments that are simpler and more specific from the point of view of calculating their trajectory. To implement this purposeful division, it is necessary to analyze the structure, identify the main components, calculate the areas of their fall during autonomous movement and introduce means of dividing these elements into the design of the stage accelerator.

Claims (1)

A method of minimizing exclusion zones for detachable parts of a multi-stage launch vehicle, which consists in the fact that at the stage of preflight preparation of a multi-stage launch vehicle, the motion parameters of the separated parts of the launch vehicle are calculated until they fall to the ground and the necessary exclusion zone is determined from the calculation results, which differs the fact that in the design of the detachable parts there are elements that differ in the degree of their destruction in the dense layers of the atmosphere after separation from the launch vehicle, for these parts the flies of the flying elements of the detachable parts calculate the zones of the necessary alienation, and after separating the detachable parts from the launch vehicle during the autonomous flight of these parts on the trajectory until they enter the dense layers of the atmosphere, they form a signal on the means of division and effect on the design of the individual parts for their physical Separation into selected elements.

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