RU2547208C1 - Airborne vehicle - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: aircraft consists of airframe and engine with exhaust nozzle. Airframe comprises parachute compartment and parachute ejector wit input connected with appropriate control unit and with moving plate coupled with the drive, its input being connected with the drive control unit output. Parachute compartment is arranged at mid top section, above moving plate and below parachute ejection control unit. Pulse engine with exhaust nozzle is additionally arranged under airframe front. Rotary sector spring-loaded shutter is arranged ahead of said nozzle. Vertical prop is arranged behind said shutter coupled therewith after the turn.

EFFECT: efficient deceleration.

1 dwg

Description

The invention relates to the field of aviation technology and can be used for braking during landing.

Known aircraft presented in the book "Combat aircraft of foreign countries of the XXI century", V. Ilyin, Ed. Asta Astrel, M., 2001, p. 38, 39. It consists of a housing, an engine and an exhaust nozzle.

The device may include a parachute consisting of a canopy, slings and a parachute ejection mechanism located in the parachute storage compartment, which is rigidly connected to the body, while the mechanism has an input connected to the output of the parachute ejection control unit. The parachute can be used for braking after landing at the airport, which reduces the mileage. Before the parachute is ejected using a movable plate that slides like a door in the elevator, a hole is formed through the drive controlled by the drive control unit, through which a parachute consisting of a canopy and slings is ejected from the parachute storage compartment using the parachute ejection mechanism. The parachute can also be used for braking during flight. However, the amount of braking is not always sufficient.

Known aircraft set out in the book of E.A. Fedosova "Aviation, Air Defense of Russia, scientific and technological progress", ed. Bustard, M., 2005, p. 388. It consists of the same nodes as the aforementioned analogue. But it also does not provide sufficient braking when moving and using a parachute. Using the proposed device increases braking when driving using a parachute and without increasing the amount of fuel.

This is achieved by placing the compartment for laying the parachute in the middle of the upper part of the body, above the compartment - the movable plate, below the compartment - the control unit for ejecting the parachute, as well as the introduction of a pulse engine at the bottom of the front of the case and a second exhaust nozzle in front of the pulse engine, a rotary sector spring damper in front of this nozzle, vertical strut behind the aforementioned damper, rigidly connected to it after turning.

In figure 1 and in the text the following notation:

1 - parachute canopy

2 - slings

3 - compartment for storing a parachute

4 - movable plate

5 - drive

6 - parachute release mechanism

7 - drive control unit

8 - parachute release control unit

9 - engine

10 - exhaust nozzle

11 - rotary sector spring damper

12 - vertical stand

13 - exhaust nozzle

14 - pulse engine

15 - case,

while the housing 15 is rigidly connected to the engine 9, rigidly connected to the exhaust nozzle 10, moreover, the housing 15 is rigidly connected to the compartment for stowing a parachute 3, which is rigidly connected to the ejection mechanism of the parachute 6, which is rigidly connected to the slings 2, which are rigidly connected to the dome of the parachute 1, and the compartment 3 also has a rigid connection with the movable plate, rigidly connected to the actuator 5, the input of which is connected to the output of the control unit of the actuator 7, in addition, the housing 15 is rigidly connected to the pulse motor 14, having a rigid connection with the second exhaust nozzle 13, vp In front of which there is a rotary sector spring damper 11, rigidly connected with the vertical strut 12 behind the damper after its rotation.

The device operates as follows.

Take-off of the device is carried out using the engine 9 (see figure 1), rigidly connected with the housing 15 and the exhaust nozzle 10 located behind the engine, through which a stream of ignited fuel comes out. For landing, for example, on sites of reduced length with the engine 9 turned off, the following nodes are introduced: a parachute consisting of a canopy of a parachute 1, a sling 2, an ejection mechanism for a parachute 6, which is located in the compartment for storing a parachute 3, which is rigidly connected to the case 15. the mechanism 6 has an input connected to the output of the parachute ejection control unit 8. The compartment for laying the parachute 3 is located in the middle of the upper part of the housing 15. Above the compartment 3 there is a movable plate 4 rigidly connected to the actuator 5 controlled by the control unit water 7. Below the compartment 3 there is a parachute ejection control unit 8. The device also includes a pulse motor 14, at the bottom of the front of the housing 15, an exhaust nozzle 13 in front of the engine 14, a rotary sector spring damper 11 located in front of the nozzle 13, and a vertical strut 12 located behind the damper, rigidly connected to the post after turning.

Sequential actions during landing are as follows.

Before the parachute is ejected using a movable plate 4, which is displaced like a door in the elevator using an actuator 5 controlled by a control unit of an actuator 7, an opening is formed in the compartment for stowing the parachute 3. The engine 14 is first turned on and, with the help of a jet of ignited fuel, the nozzle 13 acts and turning the rotary sector spring damper 11 clockwise until it contacts the vertical strut 12.

In the initial state, the shutter 11 was in contact with the nozzle 13 and a stream of air during its flight smoothly flows around it. Further, in connection with the operation of the pulse motor 14, braking occurs to a speed that ensures safe release of the parachute without rupture of the canopy 1 and sling 2, which are rigidly interconnected. The parachute is ejected using the command issued by block 8 to mechanism 6, which is rigidly connected to the slings. After that, the braking of the apparatus is further increased and its landing is carried out. At a permissible flight speed, a parachute can be ejected without first turning on the engine 14. It is also possible to perform braking using a pulse engine without using a parachute. Pulse motor increases braking compared to a continuous jet engine. When this engine 9 is turned off. An example of the execution of a pulsed motor is presented in patent No. 2403189, author A. Chasovskaya A variant is possible when ejecting a parachute after landing.

In this case, the travel time is even more reduced, and the parachute can be placed not only as described in this device, but also as described in the analogue.

The proposed device can be used when landing on sections of reduced length. This ensures an economic effect and does not increase the amount of fuel, since the main engine turns off. The device can also be used for landing in emergency situations and on the water surface. With an increased mass of the device, two or more parachutes can be used.

Thus, the use of the proposed device increases flight safety, and therefore improves the performance characteristics of aircraft.

Claims (1)

The aircraft, consisting of a body rigidly connected to the engine, rigidly connected to the exhaust nozzle, the body is also rigidly connected to the compartment for stowing the parachute, which is rigidly connected to the ejection mechanism of the parachute, rigidly connected to the slings, which are rigidly connected to the dome of the parachute, moreover the aforementioned mechanism has an input connected to the output of the parachute ejection control unit and has a rigid connection with a movable plate rigidly connected to the drive, the input of which is connected to the output of the drive control unit, which consists in placing the compartment for laying the parachute in the middle of the upper part of the body, above the compartment - the movable plate, below the compartment - the control unit for ejecting the parachute, as well as the introduction of a pulse engine at the bottom of the front of the case and a second exhaust nozzle in front of the pulse engine, a rotary sector spring flaps in front of this nozzle, a vertical strut behind the aforementioned flap, rigidly connected to it after turning.