RU2376198C1 - Flight vehicle compartment - Google Patents

Abstract

FIELD: aircraft and aerospace engineering.

SUBSTANCE: proposed flight vehicle compartment comprises skin with vent hole, spring-loaded cover pivoted in said skin vent hole. Said cover also comprises vent hole to accommodate spring-loaded flap pivoted therein flush with cover surface. Compartment skin is furnished with limit stop restricting cover travel from compartment, while cover and flap incorporates limit stop to restrict, on the one hand, flap travel into compartment to allow cover to move together with flap into compartment, and, on the other hand, flap travel into ambient medium.

EFFECT: pressure control in flight vehicle compartment in ascent/descent, and simplified design.

12 dwg

Description

The invention relates to the field of aerodynamics of aircraft (LA) and can be used in rocket science and aviation to create compartments for aircraft that fly along the trajectories of aircraft ascending and lowering.

The invention is intended to control aerodynamic pressures acting on the aircraft compartment, its elements (shell, mounting, technological hatches and other elements) and products (transportation objects, automation units of the control system, etc.) located in the compartment.

Known compartment LA, for example a compartment of an aircraft containing a shell with a drainage hole made in the shell, hingedly installed in the drainage hole of the sash, a mechanism for moving the valves with levers, providing movement of the valves to regulate the pressure in the aircraft compartment [1].

The disadvantage of this technical solution is the complexity of the structural layout of the compartment due to the presence of a shutter movement mechanism in the aircraft.

A well-known compartment of the aircraft, for example the compartment of the orbiter "Buran", containing a shell, drainage holes made in the shell of the compartment, the sash installed in the drainage holes, drives and control system of the sash [2].

The flaps are designed to reduce the pressure drops acting on the compartment shell and are equipped with a control system with actuators for closing and opening the drainage holes along the paths of raising and lowering in accordance with the shutter operation pattern fixed for the paths. The presence of controlled along the paths of the drives complicates the design of the compartment, and also necessitates linking the sequence diagram of the drive control system to the design paths. Thus complicate the structural layout of the compartment.

Known compartment LA, for example a compartment of a launch vehicle containing a shell, a drainage hole made in the shell of the compartment, a spring-loaded cover pivotally mounted in the drainage hole of the shell [3].

According to this technical solution, a spring-loaded cover configured for a given pressure drop, not exceeding the maximum allowable from the strength conditions of the compartment elements, opens due to excessive aerodynamic pressure acting on the compartment along the elevation path, without the use of drives with their control system to open the cover.

The disadvantage of this technical solution is that the pressure is not regulated along the aircraft descent trajectory. The technical solution is applicable only for missiles flying along trajectories with increasing flight altitude.

The technical solution [3] is the closest to the proposed and accepted by the authors as a prototype.

The objective of the invention is to provide pressure control in the compartment of an aircraft flying along the trajectories of ascent and descent, while simplifying the design of the compartment.

The problem is solved in such a way that in the compartment of the aircraft containing the shell with a drainage hole, a spring-loaded cover pivotally mounted in the drainage hole of the shell, according to the invention, a drainage hole is also made in the cover and a spring-loaded shutter is pivotally mounted flush with the surface of the cover, while in the shell of the compartment, a limiter for displacing the cover in the compartment is made, and in the lid and the sash there are made limiters for moving the sash separately into the compartment, which ensures the movement of the cover together with the sash first compartment and a separate wing - into the external environment.

The technical results of the invention are:

- providing pressure differences acting on the compartment during flight along the descent path, exceeding pressure differences acting on the compartment during flight along the ascending path;

- simplification of the structural layout of the compartment;

- expansion of the functionality of the compartment.

The invention is illustrated by the structural scheme of the compartment, illustrations of the movement of the lid and sash in the process of regulating the pressure in the compartment, as well as graphs of aerodynamic pressures acting on the compartment along the flight paths of the aircraft.

Figure 1 shows the layout of the compartment, its main elements are shown and a fragment of the compartment with a lid (node I) is highlighted.

Figure 2, 3, 4 shows the main elements of the fragment of the compartment with the cover, respectively, in the initial position and in the process of regulating the pressure in the compartment on the trajectories of the ascension and descent of the aircraft.

1, 3 and 4 also illustrate the direction of movement of the lid with the sash (solid arrows), separately the sash (dashed arrow) and the direction of flow of the gas medium when regulating the pressure in the compartment.

In these figures:

1 - shell;

2, 5 - drainage holes;

3 - cover;

4, 7 - hinges;

6 - sash;

8, 9, 13, 14 brackets;

10, 11, 15, 16 - holes;

12, 17 - springs;

18, 19, 20 - limiters.

Figures 5 and 6 show the dependences of the pressure drops ΔР and -ΔР acting on the compartment on the flight time t of the aircraft at various values of the effective _leaflet passage area (µS) of the _stem. and covers (µS) _cr. , respectively, for the trajectories of the ascent and descent of the aircraft, where:

S _stem , S _cr. - passage area of the sash and cover, respectively;

µ _st. , μ _cr. - flow coefficient of the passage area of the sash and cover, respectively.

The aircraft compartment (Fig. 1) contains a shell 1 in which a drainage hole 2 is made (see also Fig. 4) and a spring-loaded cover 3 is installed in it, which can be moved into the compartment on hinges 4 of the cover 3.

A drainage hole 5 is also made in the lid 3 (see also Fig. 3) and a spring-loaded sash 6 is installed in it, which can move on hinges 7 of the sash 6 both in the external environment and together with the lid 3 on the hinges 4 of the lid 3 in the compartment .

On the outer surfaces (view A) of the shell 1 and the cover 3, brackets 8 and 9 are installed, respectively, made in the form of inverted T-shaped profiles with holes 10 and 11, which provide installation and adjustment of the spring tension 12 of the cover 3.

Similarly, on the inner surfaces (view B) of the shell 1 and the sash 6, brackets 13 and 14 are also installed, also made in the form of T-shaped profiles with holes 15 and 16, providing installation and adjustment of the tension of the springs 17 of the sash 6.

In the cover 1 of the compartment, a stopper 18 for moving the cover 3 to the external medium (Fig. 4) is made, and in the cover 3 and the sash 6, the stoppers 19 and 20 of the movement of the sash 6 separately into the compartment (Fig. 3) are made. The stops 18, 19, 20 can be made in the form of ledges.

To reduce the impact of the aerodynamic flow on the springs 12 of the cover 3, they can be closed by fairings or laid in lodges made in the shell 1 and cover 3 (not shown in the drawing for simplicity).

Thus, they realize the possibility of moving the sash separately into the external environment (Fig. 3) and the lid together with the sash - into the compartment (Fig. 4), which ensures the effective passage area of the sash (µS) of the _stem. on the lifting section is less than the effective passage area of the cover (µS) _cr. on the descent section of the aircraft.

The pressure regulation in the compartment is as follows.

When aerodynamic flow flows around compartment A at a speed of V, an external P _bunk acts on the shell 1 of the compartment _. and internal R _int. pressure (figure 2, 3 and 4). The values of these pressures and their excess pressures ΔP _i depend on the parameters of the flight path of the aircraft and the operating modes of the shutter 6 and cover 3 separately, together with the shutter 6.

In the initial position, the pressure inside the compartment is equal to the external pressure

R _int. = P _nar . The cover 3 overlaps the drainage hole 2 of the shell 1 under the action of the springs 12 and is installed flush with the shell 1 of the compartment. When this casement 6 under the action of the springs 17 is installed flush with the cover 3 (figure 2, node I).

During the flight of the aircraft along the lift path inside the compartment, positive overpressure ΔP ₁ = P _int. -P _Nar. , which depends on the effective passage area (µS) of the _stem. leaf 6 and has a characteristic maximum (Fig. 5), moreover, with an increase in (µS) _stem. excess pressure ΔP decreases. Shell 1 compartment works in tension.

The decrease in positive overpressure ΔP inside the compartment along the lift path is carried out by the outflow of the gas medium from the compartment. In this case, the sash 6 under the action of positive overpressure in the compartment moves to the external environment (figure 3).

Permissible overpressure ΔP _add. inside the compartment ( _figure 5) provide a given effective passage area (µS) _stem. leaf 6, which is achieved by setting the springs 17 of the leaf 6.

After the overpressure is released from the compartment, the sash 6 closes under the action of the springs 17 of the sash 6 and takes its initial position (figure 2).

When flying aircraft along the descent trajectory inside the compartment, a negative overpressure of -ΔP ₂ = P _ext. -P _Nar. , which depends on the effective passage area (µS) _cr. cover 3 and has a characteristic minimum (Fig.6), and with an increase (µS) _cr. excess pressure -ΔP decreases. Shell 1 compartment works in compression.

The decrease in negative excess pressure -ΔP inside the compartment along the descent path is carried out by blowing the gaseous medium into the compartment. In this case, under the influence of positive excess pressure in the external environment, the sash 6 is pressed against the lid 3 and the lid 3 with the sash 6 is moved to the compartment (figure 4).

Permissible negative overpressure -ΔP _add. inside the compartment (Fig.6) provide a given effective passage area (ΔS) _cr. cover 3, which is achieved by setting the springs 12 of the cover 3.

After pressurizing the compartment, the lid 3 with the shutter 6 closes under the action of the springs 12, is pressed against the shell 1 and takes its initial position (figure 2).

Because the effective leaflet area (µS) of the _stem. less than the effective passage area of the lid (µS) _cr. , realize the pressure drops | ΔP ₁ | acting on the compartment along the ascent path, less pressure differences | ΔP ₁ | acting on the compartment along the descent path.

Thus, they provide regulation of aerodynamic pressures acting on the compartment of an aircraft flying along the paths of ascent and descent, which leads to the achievement of the task.

At the same time, in comparison with the well-known technical solutions, the structural layout of the compartment is simplified by eliminating the lid and sash movement drives controlled along the flight paths.

The functionality of the compartment also expands due to its operation as part of an aircraft flying along the paths of ascent and descent.

Currently, the technical proposal is being implemented in relation to the cargo compartment of a transport aircraft.

The possibility of using a technical solution for the cargo compartment of a spacecraft returned from the orbit of an artificial Earth satellite is analyzed.

Literature

1. US patent No. 3426984 A, 02/11/1969

2. The space complex. The reusable orbiter Buran. Ed. Yu.P. Semenova, G.E. Lozino-Lozinsky, V.L. Lapygin, V.A. Timchenko. M.: Mechanical Engineering, 1995, pp. 144-150.

3. Patent RU No. 2145563 C1, 02.20.2002

Claims (1)

Aircraft compartment, comprising a shell with a drainage hole, a spring-loaded cover pivotally mounted in the drainage hole of the shell, characterized in that the cover also has a drainage hole and a spring-loaded flap pivotally mounted therein flush with the surface of the cover, while a movement limiter is made in the compartment shell the lid from the compartment, and in the lid and the sash there are made limiters for moving the sash separately to the compartment, which ensures the movement of the lid together with the sash in the compartment and no leaf - in the external medium.

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