UA19433U - Rocket stage of shuttle rocket - Google Patents

Abstract

The utility model relates to rocket-space area. A stage of shuttle rocket has a body with propulsion compartment, a transition compartment with rotary panels, those are connected to flexible shell in toroidal shape, rocket solid-fuel engines for deceleration of the stage and parachute system attached to the bottom section of the stage. To decrease impact loads on the body the stage is equipped with additional solid fuel engine for the stage dropping, supports that crease and elastic foldable membrane. Additional solid fuel rocket engine is mounted in propulsion compartment on diametrically opposite to the supports surface of the body and is directed with nozzle from the supports. The supports are fixed on the body near the propulsion compartment with possibility of turn in long vertical plane, and each elastic membrane is fixed between the support and the body with formation of side sail.

Description

Description of the invention

The useful model refers to the rocket and space industry, and more specifically to the parts of rockets that return 2, and can be used during the design of reusable launch vehicles.

The stage of a reusable rocket is known, which contains a body with a propulsion compartment, a transition compartment made of rotating panels that are attached to a flexible shell of toroidal shape, and a parachute system attached to the bottom part of the stage | see patent of Ukraine Mo3737y, IPC 8640 1/00, g428 15/00, 2004). The filling of the flexible shell is carried out by inflation gases, which are contained in the tanks of the stage. The filled 70 flexible shell, together with the rotating panels of the transition compartment, forms a stabilizing device in flight, and during landing is used as a device for landing the stage. To brake the stage during separation, solid propellant rocket engines (RDTP) are used | see the book by K.S. Kolesnikov et al. "Dynamics of separation of stages of aircraft apparatus", M., Mashinostroenie, 1977, p. 11 fig. 1.61.

The disadvantage of the well-known rocket stage is its low operational qualities, because during landing, the stage bounce is possible, and after landing, the stage remains in a vertical position, while there is a danger of it falling (collapsing) and damaging the side surface of the body due to landing on uneven ground and wind action

The closest to the proposed one in terms of technical solution is the stage of the reusable rocket chosen as a prototype, which is described in the patent of Ukraine Mo13357y, IPC 8640 1/00, 428 15/00, 2005.

The specified stage contains a body with a propulsion compartment, a transition compartment made of rotating panels that are attached to a flexible shell of toroidal shape, solid propellant rocket engines for braking the stage and a parachute system attached to the bottom part of the stage. In order to increase landing safety and eliminate rebound, the step is equipped with a movable ring base, which is attached: to the rotating panels of the transition compartment with the help of rotary nodes, to the body of the step with the help of shear pins and to the damping device. shsh

The disadvantage of the known step is its poor performance due to the possibility of the step falling (overturning) as a result of landing on uneven ground and wind.

The basis of the useful model is the task of creating an improved design of the stage of a reusable rocket, which would allow reducing shock loads on its body by introducing elements of new and technical solutions into it, such as: so - the presence of supports that are folded and fixed on the body near propulsion compartment with the possibility of rotation in the longitudinal vertical plane, which allows to exclude damage to the body of the stage during its M filling, and their rotation allows to ensure the minimum dimensions of the stage during flight; Ф - the presence of an additional RDTP for stair collapse, which is mounted in the engine compartment on the surface of the hull diametrically opposite to the supports and directed by a nozzle from the supports, which allows you to ensure - the stair collapse in a given direction and use one set of supports, and its placement in the engine compartment allows you to create the maximum moment relative to the Earth's surface for grade collapse; - the presence of elastic membranes, which are folded and each of which is fixed between the support and the hull, "forming a side sail, which allows you to orientate the degree according to the wind and, thus, use the supports most efficiently Z 70 during backfilling. c The task is solved in such a way that the proposed stage of the rocket is reusable

Of" use, which contains a body with a propulsion compartment, a transition compartment with rotating panels that are connected to a flexible toroidal shell, solid propellant rocket motors for braking the stage and a parachute system attached to the bottom part of the stage, it is equipped with an additional solid propellant engine for filling the stage, with supports that crumple and an elastic membrane that folds, while - an additional solid fuel rocket engine is mounted in the propulsion compartment on the surface of the hull diametrically (se) opposite to the supports and directed by a nozzle from the supports, the supports are fixed on the housing near the propulsion compartment with the possibility of rotation in the longitudinal vertical plane, and each elastic membrane is fixed between the shk support and the hull, forming a side sail. со 20 To explain the construction of the stage and its work, drawings and its detailed description are attached. The drawings show: c" - in Fig. 1 - a general view of the stage of a reusable rocket before landing; - in Fig. 2 - section A-A of Fig. 1 (transverse section of a step); - in Fig. 3 - a general view of the stage of the rocket after flooding. 29 The proposed stage of a reusable rocket includes a body 71 with a propulsion compartment 2, a transitional compartment made of rotating panels 3, fastened with a flexible shell 4 of toroidal shape, a parachute system 5, solid fuel rocket engines 6, an additional RDTP 7 installed in the propulsion compartment 2, and rotary supports 8, which are crumpled, with elastic membranes 9, fixed on the body 1. The stage of the reusable rocket makes a landing on the surface 10 of the Earth. The direction of the wind is shown by arrow B. 60 Landing of the proposed multi-use stage is carried out as follows.

In the active part of the rocket flight, after turning off the propulsion unit of the reusable stage, the separation of the stage occurs by braking with the help of the RDTP 6, while the pivot supports 8 and elastic membranes 9 are folded along the body 1. In the passive part of free fall, the flexible shell 4 is filled with gas, and together with the rotary panels of the transition compartment, it forms a stabilizing device that provides preliminary braking and atmospheric descent of the body 1 in an oriented position - with the propulsion compartment 2 forward. Then the parachute system 5 is opened, which provides further braking of the stage, while the parachute system 5 is hooked onto the propulsion compartment 2. In the area of the parachute descent, the rotary supports 8 are set in the landing position by turning in the longitudinal vertical plane, while stretching the elastic membranes 9 with the formation side sail Acting on the elastic membranes 9, the wind turns the step in such a way that the additional RDTP 7 turns out to be directed towards the wind (Fig. 1, 2). After touching the surface 10 of the Earth with the flexible shell 4, the parachute system 5 is fired, the additional RDTP 7 is turned on, which ensures the collapse of the stage on the rotary supports 8. At the same time, thanks to the orientation of the additional RDTP 7 towards the wind, the collapse is carried out in the most favorable 7/0 direction - downwind . Pivot supports 8 during contact with the surface 10 of the Earth crumple and dampen shock loads from the energy of the stage collapse (Fig. 3). Swivel supports 8 are located near the propulsion compartment 2, because it has a large weight of up to 10 tons.

In the process of lowering the stage, elastic membranes are heated to 300 °C, so they can be made of Armid-T material, the working temperature of which reaches 10002 °C. The duration of high temperatures is up to 10 minutes.

Thus, the proposed degree of multiple use, which has a simple and reliable design, allows you to increase the safety of its landing in conditions of wind and reduce its weight due to weight reduction

Road accident for filling.

Claims (1)

The formula of the invention is a stage of a reusable rocket containing a body with a propulsion compartment, a transition compartment with rotating panels, which are connected to a flexible shell of toroidal shape, solid propellant rocket engines for braking the stage and a parachute system attached to the bottom part of the stage, which differs from WHEREAS, it is equipped with an additional solid propellant engine for stage collapse, collapsible props, and an elastic membrane that folds, while the additional solid propellant rocket motor c) is mounted in the propulsion compartment on the surface of the hull diametrically opposite to the props and directed by a nozzle from the props, the struts are fixed to the hull near the propulsion compartment with the possibility of rotation in the longitudinal vertical plane, and each elastic membrane is fixed between the strut and the hull, forming a side sail. so (ze) « (o) yo - and? - se) sh» (95) syu» 60 b5