阅读说明：本技术 一种直升机及弹射逃生缓冲装置 (Helicopter and ejection escape buffering device ) 是由 陈延礼 程延耕 王辉 白桂强 杜卫康 李秋实 罗松松 于 2019-11-15 设计创作，主要内容包括：一种直升机及弹射逃生缓冲装置属于直升机逃生装置技术领域,目的在于解决现有技术存在的直升机在遇到坠毁时弹射过程复杂、安全系数低以及防护性能差的问题。本发明的一种直升机包括：机体；和所述机体可拆卸连接的驾驶舱；设置在所述机体和驾驶舱的连接处实现机体和驾驶舱连接或脱离的连接保护装置；以及设置在驾驶舱上靠近机体和驾驶舱的连接处一端的分离缓冲装置,通过所述分离缓冲装置的火箭弹射器和降落伞的作用降低驾驶舱降落以及着陆的速度。(The utility model provides a helicopter and launch buffer of fleing belongs to helicopter escape device technical field, and aim at solves the problem that the helicopter that prior art exists launches the complicated, factor of safety low and barrier propterty of process when running into the crash. A helicopter of the present invention includes: a body; the cockpit is detachably connected with the machine body; the connection protection device is arranged at the connection part of the machine body and the cockpit to realize connection or disconnection of the machine body and the cockpit; and the separation buffer device is arranged at one end of the cockpit, which is close to the connection part of the engine body and the cockpit, and reduces the landing speed of the cockpit through the action of the rocket catapult and the parachute of the separation buffer device.)

1. A helicopter, comprising:

a body (3);

it is characterized by also comprising:

a cockpit (1) detachably connected to the body (3);

the connection protection device is arranged at the joint (2) of the machine body (3) and the cockpit (1) to realize connection or disconnection of the machine body (3) and the cockpit (1);

and the separation buffer device is arranged at one end of the cockpit (1) close to the connection part (2) of the machine body (3) and the cockpit (1), and the landing speed of the cockpit (1) is reduced through the separation buffer device.

2. A helicopter according to claim 1, characterized in that said connection protection means comprise:

a first rolling guide rail (4) fixed on the machine body (3) through a fixing hole (401);

the second rolling guide rail (7) is in sliding fit with the first rolling guide rail (4), and the second rolling guide rail (7) is fixed on the cockpit (1);

a fixed frame (5) fixed on the cockpit (1);

the connecting and disconnecting mechanism (6) is arranged on the fixed frame (5), and the first rolling guide rail (4) can be opened or locked in a sliding motion relative to the second rolling guide rail (7) through the connecting and disconnecting mechanism (6).

3. A helicopter according to claim 2, characterized in that said connection and disconnection mechanism (6) comprises:

the positioning block (601) is arranged in the fixing frame (5), and the positioning block (601) penetrates through the fixing frame (5) to be matched with a corresponding taper hole in the first rolling guide rail (4) in a plugging manner;

one end of the spring (602) is in contact with one end of the fixing frame (5) close to the first rolling guide rail (4), and the other end of the spring (602) is in contact with a shaft shoulder of the positioning block (601);

and the limit switch is used for limiting the axial displacement of the positioning block (601) so that the positioning block (601) extends into the corresponding taper hole on the first rolling guide rail (4) or is separated from the taper hole.

4. A helicopter according to claim 3, characterized in that said limit switch comprises:

one end of the limiting hook (604) is in rotating fit with the fixed frame (5) through a pin (603), and the other end of the limiting hook (604) is in a hook shape;

a limiting block (605) which is in rotary fit with the fixing frame (5) at the middle position, when the positioning block (601) is positioned at the lower limit position and is matched with a corresponding taper hole on the first rolling guide rail (4), the spring (602) is in a compressed state, one end of the limiting block (605) is matched with the hook-shaped end of the limiting hook (604), the other end of the limiting block (605) is contacted with the upper end face of the positioning block (601), the positioning block (601) is pressed tightly, and the upward displacement of the positioning block (601) is limited;

and the electromagnetic coil (606) and one hooked end of the limiting hook (604) are oppositely arranged, the limiting hook (604) is attracted by electrifying the electromagnetic coil (606), the limiting hook (604) is separated from the limiting block (605) at the hooked end of the limiting hook (604), and the positioning block (601) is released.

5. A helicopter according to any of claims 1 to 4, characterized in that said decoupling cushioning means comprise:

the two rocket ejectors (8) are symmetrically arranged on two sides of the cockpit (1);

and the parachute (9), the parachute (9) sets up the junction (2) of organism (3) and cockpit (1).

6. An ejection escape buffer device is characterized by comprising a connection protection device and a separation buffer device which are used for realizing the connection or the separation of two structures, wherein the separation buffer device is used for reducing the speed of one of the two structures to be protected for landing in the air;

the connection protection device includes:

a first rolling guide (4) fixed to the one structure by a fixing hole (401);

a second rolling guide rail (7) in sliding fit with the first rolling guide rail (4), wherein the second rolling guide rail (7) is fixed on the other structure;

a fixing frame (5) fixed on the other structure;

the connecting and disconnecting mechanism (6) is arranged on the fixed frame (5), and the first rolling guide rail (4) is opened or locked in a sliding motion relative to the second rolling guide rail (7) through the connecting and disconnecting mechanism (6);

the separation buffer device includes:

the two rocket ejectors (8) are symmetrically arranged on two sides of one of the two structures to be protected;

and a parachute (9), the parachute (9) being arranged at the junction (2) of the one structure and the other structure.

7. The ejection escape buffering device of claim 6, wherein the connection and disconnection mechanism (6) comprises:

the positioning block (601) is arranged in the fixing frame (5), and the positioning block (601) penetrates through the fixing frame (5) to be matched with a corresponding taper hole in the first rolling guide rail (4) in a plugging manner;

one end of the spring (602) is in contact with one end of the fixing frame (5) close to the first rolling guide rail (4), and the other end of the spring (602) is in contact with a shaft shoulder of the positioning block (601);

and the limit switch is used for limiting the axial displacement of the positioning block (601) so that the positioning block (601) extends into the corresponding taper hole on the first rolling guide rail (4) or is separated from the taper hole.

8. The ejection escape buffer of claim 7 wherein said limit switch comprises:

one end of the limiting hook (604) is in rotating fit with the fixed frame (5) through a pin (603), and the other end of the limiting hook (604) is in a hook shape;

a limiting block (605) which is in rotary fit with the fixing frame (5) at the middle position, when the positioning block (601) is positioned at the lower limit position and is matched with a corresponding taper hole on the first rolling guide rail (4), the spring (602) is in a compressed state, one end of the limiting block (605) is matched with the hook-shaped end of the limiting hook (604), the other end of the limiting block (605) is contacted with the upper end face of the positioning block (601), the positioning block (601) is pressed tightly, and the upward displacement of the positioning block (601) is limited;

and the electromagnetic coil (606) and one hooked end of the limiting hook (604) are oppositely arranged, the limiting hook (604) is attracted by electrifying the electromagnetic coil (606), the limiting hook (604) is separated from the limiting block (605) at the hooked end of the limiting hook (604), and the positioning block (601) is released.

Technical Field

The invention belongs to the technical field of helicopter escape devices, and particularly relates to a helicopter and an ejection escape buffering device.

Background

Aiming at helicopter safety protection measures, different measures are adopted in the prior art; such as installing ejector seats, roll cage designs, cushioning structures for helicopter seats, and airbags.

With respect to the ejector seat, only two helicopters, card-50 and card-52, among the numerous helicopters in the world, are equipped with ejector seats. Other helicopters are not equipped with ejection seats because of their special construction, their flight deck tips are rotors, which make ejection more complicated. In addition, the general flying height of the helicopter is low, if mechanical failure occurs in the flying process or the helicopter is hit by enemy weapons, loses control and cannot fly, the complicated ejection process is easy to cause problems and often crashes before ejection; therefore, the safety protection of the helicopter is generally designed by the fuselage.

For other helicopters, the structural design similar to that of a rolling cage of a racing car and the cushioning structure of a seat of the helicopter are only used for ensuring the life safety of a person falling from the helicopter, and the rolling cage of the racing car is that the racing car rolls even on the ground for a plurality of circles under the conditions that the racing car turns rapidly and rushes out of a runway and the like. In order to reduce the injury to people in case of rolling, the racing cars are provided with rolling frames, so that the driving space of a racing driver can not be seriously extruded when the racing cars roll, and the personal safety is protected. After the helicopter falls, the helicopter is usually easy to roll (generally does not roll for several turns like a racing car, generally lands on the side and reaches 90 degrees), and if the helicopter falls on a mountain slope, the rolling state of the helicopter is uncertain. In order to protect the life safety of the driver, some helicopters are designed with a relatively rigid frame to protect the safety space of the driver. The problem with this current design is that the safety protection is extremely limited, at best to ensure that the driver is not mechanically jammed by the deformation of the cabin. In the process of falling, the sudden change of the speed when falling to the ground can cause the internal organs to bear larger impact and can also cause casualties.

The safety air bags equipped on some helicopters prevent the instrument from flying to hurt people when falling, and reduce impact. Such as the eagle helicopter, equipped with a rear three-point fixed landing gear with a heavy shock absorber, which absorbs 60% of the impact energy upon crash. The protection device in the form only buffers when crashed, has no way of reducing the crashing impact force, and has poor protection performance.

Disclosure of Invention

The invention aims to provide a helicopter and an ejection escape buffering device, and solves the problems that in the prior art, the ejection process of the helicopter is complex, the safety coefficient is low and the protective performance is poor when the helicopter is crashed.

To achieve the above object, a helicopter of the present invention comprises:

a body;

the cockpit is detachably connected with the machine body;

the connection protection device is arranged at the connection part of the machine body and the cockpit to realize connection or disconnection of the machine body and the cockpit;

and the separation buffer device is arranged at one end of the cockpit, which is close to the connection part of the machine body and the cockpit, and reduces the landing speed of the cockpit through the separation buffer device.

The connection protection device includes:

the first rolling guide rail is fixed on the machine body through a fixing hole;

the second rolling guide rail is in sliding fit with the first rolling guide rail and is fixed on the cockpit;

the fixing frame is fixed on the driving cabin;

and the connecting and separating mechanism is arranged on the fixed frame, and the opening or locking of the sliding motion of the first rolling guide rail relative to the second rolling guide rail is realized through the connecting and separating mechanism.

The connection and disconnection mechanism includes:

the positioning block penetrates through the fixed frame and is in plug fit with the corresponding taper hole on the first rolling guide rail;

one end of the spring is in contact with one end of the fixing frame close to the first rolling guide rail, and the other end of the spring is in contact with a shaft shoulder of the positioning block;

and the limit switch is used for limiting the axial displacement of the positioning block, so that the positioning block extends into the corresponding taper hole on the first rolling guide rail or is separated from the taper hole.

The limit switch includes:

one end of the limiting hook is in rotating fit with the fixing frame through a pin, and the other end of the limiting hook is in a hook shape;

the limiting block is in rotary fit with the fixing frame at the middle position, when the positioning block is positioned at the lower limit position and is matched with the corresponding taper hole on the first rolling guide rail, the spring is in a compressed state, one end of the limiting block is matched with the hook-shaped end of the limiting hook, the other end of the limiting block is in contact with the upper end face of the positioning block, the positioning block is pressed tightly, and upward displacement of the positioning block is limited;

and the electromagnetic coil and one hooked end of the limiting hook are oppositely arranged, and the electromagnetic coil is electrified to attract the limiting hook, so that the limiting block at the hooked end of the limiting hook is separated, and the positioning block is released.

The separation buffer device includes:

the two rocket ejectors are symmetrically arranged on two sides of the cockpit;

and the parachute is arranged at the joint of the machine body and the cockpit.

An ejection escape buffer device comprises a connection protection device and a separation buffer device which realize the connection or disconnection of two structures, and the separation buffer device reduces the speed of one of the two structures to be protected for landing in the air;

the connection protection device includes:

a first rolling guide fixed to the one structure through a fixing hole;

a second rolling guide rail in sliding fit with the first rolling guide rail, the second rolling guide rail being fixed to the other structure;

a mount secured to the other structure;

the connecting and disconnecting mechanism is arranged on the fixed frame, and the first rolling guide rail is opened or locked relative to the second rolling guide rail in a sliding motion through the connecting and disconnecting mechanism;

the separation buffer device includes:

the two rocket ejectors are symmetrically arranged on two sides of one of the two structures to be protected;

and a parachute disposed at a junction of the one structure and the other structure.

The connection and disconnection mechanism includes:

the positioning block penetrates through the fixed frame and is in plug fit with the corresponding taper hole on the first rolling guide rail;

one end of the spring is in contact with one end of the fixing frame close to the first rolling guide rail, and the other end of the spring is in contact with a shaft shoulder of the positioning block;

and the limit switch is used for limiting the axial displacement of the positioning block, so that the positioning block extends into the corresponding taper hole on the first rolling guide rail or is separated from the taper hole.

The limit switch includes:

one end of the limiting hook is in rotating fit with the fixing frame through a pin, and the other end of the limiting hook is in a hook shape;

the limiting block is in rotary fit with the fixing frame at the middle position, when the positioning block is positioned at the lower limit position and is matched with the corresponding taper hole on the first rolling guide rail, the spring is in a compressed state, one end of the limiting block is matched with the hook-shaped end of the limiting hook, the other end of the limiting block is in contact with the upper end face of the positioning block, the positioning block is pressed tightly, and upward displacement of the positioning block is limited;

and the electromagnetic coil and one hooked end of the limiting hook are oppositely arranged, and the electromagnetic coil is electrified to attract the limiting hook, so that the limiting block at the hooked end of the limiting hook is separated, and the positioning block is released.

The invention has the beneficial effects that: when the helicopter fails or is attacked by armed force, the body and the cockpit can be quickly separated, and the cockpit can quickly fly forwards away from the body. Usually, when the cockpit is separated from the body, the front and back forces of the helicopter are unbalanced, the helicopter starts to move in elevation, and therefore the propeller cannot hit the cockpit. When the helicopter fails or encounters an attack, a driver triggers a switch immediately, rocket ejectors taking gunpowder as power on two sides in the helicopter start to work, a cockpit is quickly separated from a machine body on a second rolling slide rail relative to a first rolling slide rail at an acceleration of nearly 400g, the rocket ejectors stop working after leaving an area which cannot be covered by a propeller of the machine body, a parachute is quickly opened, and the rocket ejectors are opened and reversely ejected from an outlet at the front end of the cockpit when landing quickly, so that the landing speed is reduced. An air bag is also arranged on the instrument panel of the helicopter, and a buffer seat is arranged in the cab, so that the damage degree is reduced.

Drawings

FIG. 1 is a diagrammatic view of a helicopter of the present invention;

FIG. 2 is a diagram of a helicopter cockpit and airframe separation process of the present invention;

FIG. 3 is a schematic view of a helicopter cockpit and airframe of the present invention shown separated;

FIG. 4 is a schematic view of the connection protection device according to the present invention;

FIG. 5 is an end view of a first rolling guide of the present invention;

FIG. 6 is a schematic view of the installation of the separation buffer device in the cockpit according to the present invention;

FIG. 7 is an end view of the separation bumper of the present invention installed in the cockpit;

FIG. 8 is a schematic view of a process for reducing the landing gear of the cockpit utilizing the present invention;

wherein: 1. the device comprises a cockpit, 2, a joint of the cockpit and the machine body, 3, the machine body, 4, a first rolling guide rail, 401, a fixing hole, 5, a fixing frame, 6, a connection and disconnection mechanism, 601, a positioning block, 602, a spring, 603, a pin, 604, a limiting hook, 605, a limiting block, 606, an electromagnetic coil, 7, a second rolling guide rail, 8, a rocket ejector, 9 and a parachute.

Detailed Description

The following further describes embodiments of the present invention with reference to the drawings.

The propellers are arranged on the helicopter, so if the helicopter is ejected upwards to escape, the helicopter needs to avoid the impact of the propellers. Under the normal condition, the helicopter generally flies forwards, and if the helicopter is ejected to two sides for escape, because the two sides can not be depended by the helicopter seats, the helicopter does not accord with the human body stress science, and does not accord with the principle that the speed of the airplane is far away from the body 3. Therefore, forward ejection escape can be selected to better utilize the forward flying speed of the helicopter.

Referring to fig. 1-3, a helicopter of the present invention comprises:

a machine body 3;

a cockpit 1 detachably connected to the body 3;

the connection protection device is arranged at the connection part 2 of the machine body 3 and the cockpit 1 to realize connection or disconnection of the machine body 3 and the cockpit 1;

and the separation buffer device is arranged at one end of the cockpit 1, which is close to the connection part 2 of the machine body 3 and the cockpit 1, and the landing speed of the cockpit 1 is reduced through the separation buffer device.

The connection protection device described with reference to fig. 4 and 5 comprises:

a first rolling guide 4 fixed to the body 3 through a fixing hole 401;

the second rolling guide rail 7 is in sliding fit with the first rolling guide rail 4, and the second rolling guide rail 7 is fixed on the cockpit 1;

a fixed mount 5 fixed on the cockpit 1;

and the connecting and disconnecting mechanism 6 is arranged on the fixed frame 5, and the first rolling guide rail 4 is opened or locked relative to the second rolling guide rail 7 in a sliding motion through the connecting and disconnecting mechanism 6.

The connection and disconnection mechanism 6 includes:

the positioning block 601 is arranged in the fixed frame 5, and the positioning block 601 penetrates through the fixed frame 5 and is in plug-pull fit with the corresponding taper hole on the first rolling guide rail 4;

one end of the spring 602 is in contact with one end of the fixed frame 5 close to the first rolling guide rail 4, and the other end of the spring 602 is in contact with a shaft shoulder of the positioning block 601;

and the limit switch is used for limiting the axial displacement of the positioning block 601, so that the positioning block 601 extends into the corresponding taper hole on the first rolling guide rail 4 or is separated from the taper hole.

The limit switch includes:

one end of the limiting hook 604 is in rotating fit with the fixed frame 5 through a pin 603, and the other end of the limiting hook 604 is in a hook shape;

a limiting block 605 which is in a rotary fit with the fixing frame 5 at the middle position, when the positioning block 601 is positioned at the lower limit position and is matched with the corresponding taper hole on the first rolling guide rail 4, the spring 602 is in a compressed state, one end of the limiting block 605 is matched with the hook-shaped end of the limiting hook 604, the other end of the limiting block 605 is contacted with the upper end surface of the positioning block 601, the positioning block 601 is pressed tightly, and the upward displacement of the positioning block 601 is limited;

and the electromagnetic coil 606 is opposite to one hooked end of the limiting hook 604, the limiting hook 604 is attracted by electrifying the electromagnetic coil 606, the limiting block 605 at one hooked end of the limiting hook 604 is separated, and the positioning block 601 is released.

Referring to fig. 6 and 7, the separation buffer device includes:

the rocket ejectors 8 are symmetrically arranged on two sides of the cockpit 1; the rocket ejectors 8 are fixed on two sides below the cockpit 1 in different fixing modes, and can be fixed to the lower position in the cockpit by bolt connection as long as the rocket ejectors can be fixed;

and a parachute 9, wherein the parachute 9 is arranged at the joint 2 of the machine body 3 and the cockpit 1.

The vector nozzles 801 on the rocket ejector 8 realize the ejection in different directions at different moments, and the direction of the vector nozzles 801 can be adjusted within a certain angle, and the direction is adjusted to be aligned with the moving direction of the cockpit during free falling, so that the landing impact is reduced as much as possible.

An ejection escape buffer device comprises a connection protection device and a separation buffer device which realize the connection or disconnection of two structures, and the separation buffer device reduces the speed of one of the two structures to be protected for landing in the air;

the connection protection device includes:

a first rolling guide 4 fixed to the one structure through a fixing hole 401;

a second rolling guide rail 7 in sliding fit with the first rolling guide rail 4, wherein the second rolling guide rail 7 is fixed on the other structure;

a fixing frame 5 fixed on the other structure;

the connecting and disconnecting mechanism 6 is arranged on the fixed frame 5, and the first rolling guide rail 4 is opened or locked in a sliding motion relative to the second rolling guide rail 7 through the connecting and disconnecting mechanism 6;

the separation buffer device includes:

the rocket ejectors 8 are symmetrically arranged on two sides of one of the two structures to be protected;

and a parachute 9, the parachute 9 being disposed at the junction 2 of the one structure and the other structure.

The connection and disconnection mechanism 6 includes:

the positioning block 601 is arranged in the fixed frame 5, and the positioning block 601 penetrates through the fixed frame 5 and is in plug-pull fit with the corresponding taper hole on the first rolling guide rail 4;

one end of the spring 602 is in contact with one end of the fixed frame 5 close to the first rolling guide rail 4, and the other end of the spring 602 is in contact with a shaft shoulder of the positioning block 601;

and the limit switch is used for limiting the axial displacement of the positioning block 601, so that the positioning block 601 extends into the corresponding taper hole on the first rolling guide rail 4 or is separated from the taper hole.

The limit switch includes:

one end of the limiting hook 604 is in rotating fit with the fixed frame 5 through a pin 603, and the other end of the limiting hook 604 is in a hook shape;

a limiting block 605 which is in a rotary fit with the fixing frame 5 at the middle position, when the positioning block 601 is positioned at the lower limit position and is matched with the corresponding taper hole on the first rolling guide rail 4, the spring 602 is in a compressed state, one end of the limiting block 605 is matched with the hook-shaped end of the limiting hook 604, the other end of the limiting block 605 is contacted with the upper end surface of the positioning block 601, the positioning block 601 is pressed tightly, and the upward displacement of the positioning block 601 is limited;

and the electromagnetic coil 606 is opposite to one hooked end of the limiting hook 604, the limiting hook 604 is attracted by electrifying the electromagnetic coil 606, the limiting block 605 at one hooked end of the limiting hook 604 is separated, and the positioning block 601 is released.

Referring to fig. 8, during the flight of the helicopter, once a flight fault occurs, a pilot can press the ejection escape button for the first time to electrify the electromagnetic coil 606 and attract the limit hook 604, so that the limit block 605 loses the function of blocking the spring 602 and the positioning block 601. The positioning block 601 moves upwards under the action of the spring 602 and no longer blocks the first rolling guide 4. The rolling guide is fixed on the machine body 3 through a rolling guide fixing hole 401, and the pin 603 is fixed on the fixing frame 5. The electromagnetic coil 606 and the fixing frame 5 are fixed to the cab 1. Meanwhile, the rocket ejector 8 is ignited to work, and the cockpit 1 is rapidly pushed to be separated from the machine body 3 at the acceleration of 400 g.

After the cockpit 1 is separated from the first rolling guide rail 4, the residual lift force of the propeller can enable the helicopter to start elevation motion, when the cockpit 1 is separated from the machine body 3 by a certain safety distance, the rocket ejector 8 stops working, the parachute 9 is opened, when the cockpit 1 is separated from the ground by a certain distance, the rocket ejector 8 starts working again, forward recoil is started, and the auxiliary parachute 9 reduces the landing speed as much as possible. After the instrument panel air bag and the buffer seat contact the ground, the instrument panel air bag and the buffer seat are the last protective barrier.