RU2244665C2 - Descent spacecraft - Google Patents

Abstract

FIELD: rocketry and space engineering; small descent spacecraft injected into orbit by ballistic missiles removed from combat duty.

SUBSTANCE: proposed descent spacecraft has case, control members for its orientation in space and units for coupling with launch vehicle. Plane of connection of descent spacecraft with launch vehicle coincides with transversal plane of symmetry of case of spacecraft and its diameter coincides in this plane with transversal diameter of launch vehicle. Descent spacecraft case is made in form of body obtained by rotation of oval around its larger axis and said plane of connection with launch vehicle coincides with plane of smaller axis of oval.

EFFECT: increased volume of descent spacecraft at limited transversal diameter of launch vehicle.

1 dwg, 1 tbl

Description

The invention relates to the field of rocket and space technology, and in particular to small descent spacecraft (weighing 0.1-0.2 of the mass of the Vostok type apparatus) launched into low Earth orbit using ballistic missiles taken from combat duty from the Strategic Missile Forces arsenal and Navy.

The invention can find wide application in the conversion process of the defense industry.

A wide class of ballistic and semi-ballistic type of spacecraft (SCA) is known in space technology (see, for example, V.A. Andreevsky. Dynamics of spacecraft descent to Earth. M., Mechanical Engineering., 1970, p. 18-19 )

Known devices have a disadvantage due to the fact that when landing they use a parachute system, which leads to an increase in the overall mass parameters of the device.

The closest in technical essence to the claimed object and selected as a prototype is the spacecraft of the Vostok system, in which the hull is made in the form of a body of revolution (specifically a ball) having a center of symmetry, equipped with controls for its orientation in space and docking nodes with the launch vehicle casing, the plane of the junction of the launch vehicle casing with the launch vehicle casing coinciding with the transverse plane of symmetry of the launch vehicle casing, and the diameter of the launch casing about the apparatus in the indicated plane coincides with the diameter of the carrier rocket’s body (see V.I. Feodosiev. Fundamentals of rocket flight technology. M., Science, Main Edition of Physics and Mathematics., 1981, p. 73, Fig. 2.14 )

When launching spacecraft into orbit with the help of launch vehicles from the Strategic Missile Forces and the Navy arsenals, severe restrictions are imposed on the dimensions of spacecraft, especially on the diameter, due to the need to ensure the launch of rockets from regular launch mines and to ensure stabilization of movement using a standard control system.

The prototype spacecraft due to these limitations must have dimensions not exceeding the diameter of the launch vehicle.

It follows from the above that the internal volume of the apparatus in which the payload put into orbit is placed is small and, in many cases, insufficient to accommodate all the necessary equipment intended, for example, for receiving medical preparations, growing crystals, etc.

This is the main disadvantage of the known spacecraft.

The aim of the present invention is to increase the volume of the device with a limited diameter of the launch vehicle, which displays the device into orbit.

This goal is achieved by the fact that in the known descent spacecraft containing a body made in the form of a body of revolution, having a center of symmetry, equipped with controls for its orientation in space and docking nodes with the body of the launch vehicle, the plane of the junction of the body of the spacecraft with the rocket body -carrier coincides with the transverse plane of symmetry of the lander’s hull, and the diameter of the lander’s hull in the specified plane coincides with the diameter of the launcher’s hull, rpus lander configured as a body obtained by rotating an oval about its major axis, and the joint plane with a booster housing coincides with the plane passing through the minor axis of the oval.

The presence of distinctive features in comparison with the prototype confirms the novelty of the claimed device.

Among the known technical solutions, no significant features were found that are similar to the features that distinguish the claimed solution from the prototype, therefore, it satisfies the criterion of “Significant differences”.

The set of essential features of the proposed technical solution provides an increase in the length of the apparatus, which allows to achieve the goal of the invention is to increase the volume of the apparatus with a limited diameter of the launch vehicle.

The drawing shows the body of the prototype apparatus (1) and the proposed apparatus with controls (3) on the launch vehicle (4).

The main parameters of the proposed apparatus, characterizing the technical essence of the invention, are shown in table 1, where, for comparison, the characteristics of the prototype apparatus are given.

Table 1. Parameter Name Value offers SKA SKA prototype 1. The ratio of the small and large axis of symmetry of the apparatus. 0.15-0.7 1 2. The relative volume of the apparatus for a given diameter of the launch vehicle. 1,0 0.5 Notes:
1. An oval is a closed convex plane curve (see Moscow, Sovetskaya Encyclopedia Publishing House, 1974, Volume 18). 2. The proposed device is intended as a small satellite for receiving products in microgravity space conditions of a deep vacuum: ultrapure substances of complex drugs, ideal crystals, etc. 3. The proposed device is intended for launching into orbit mainly with the help of launch vehicles of the Navy, starting during combat use from an underwater position.

The proposed descent spacecraft operates as follows.

Using a propulsion system, the device brakes in orbit and makes the transition to a descent trajectory that reaches the boundaries of a dense atmosphere in less than one revolution in orbit.

Before entering the dense layers of the atmosphere, SKA, using the controls, unfolds with a large axis of symmetry perpendicular to the velocity vector of its center of mass. Due to the aerodynamic properties, this orientation of the SKA is maintained during the entire movement in the atmosphere, due to which the maximum effect of aerodynamic drag is achieved.

The calculations showed that for a given diameter of the launch vehicle and a ratio of the axis of symmetry close to the prototype (~ 0.7), the volume of the proposed apparatus increases by at least two times, while the ballistic coefficient of the apparatus increases by more than two times, i.e. . its braking properties are improved upon descent from orbit.

Claims (1)

A descent spacecraft containing a body made in the form of a body of revolution having a center of symmetry, equipped with controls for its orientation in space and docking nodes with the body of the launch vehicle, the plane of the junction of the body of the launch vehicle with the body of the launch vehicle matching the transverse plane of symmetry of the body descent vehicle, and the diameter of the housing of the descent vehicle in the indicated plane coincides with the diameter of the housing of the launch vehicle, characterized in that the housing of the descent vehicle in a full body obtained by rotating an oval about its major axis, and the joint plane with a booster housing coincides with the plane passing through the minor axis of the oval.