阅读说明：本技术 一种稠密大气中高速飞行回转体用全包两级对开分离舱 (Full-enclosed two-stage split separation cabin for high-speed flight rotary body in dense atmosphere ) 是由 王美聪 姬永强 张怀宇 石运国 李伯阳 甄文强 王晓莉 王硕 杨鑫 何衍儒 陈强 于 2021-10-15 设计创作，主要内容包括：本发明公开了一种稠密大气中高速飞行回转体用全包两级对开分离舱,包括前壳体左半壳体、前壳体右半壳体、后壳体左半壳体、后壳体右半壳体；前壳体左半壳体的尾端和后壳体左半壳体的首端之间可转动连接；前壳体右半壳体的尾端和后壳体右半壳体的首端之间可转动连接；分离冲量装置设置在前壳体左半壳体和前壳体右半壳体之间。当回转体在稠密大气中高速飞行时,采用本申请提出的全包两级对开分离舱,在不增加分离舱结构和分离装置复杂性的前提下,可大大降低第一级对开分离时分离冲量装置需要克服的气动阻力矩,而且通过环形弧面的设计可充分利用来流的作用实现第二级对开分离,可明显提高分离舱对开分离的可靠性。(The invention discloses a full-package two-stage split separation cabin for a high-speed flying rotary body in dense atmosphere, which comprises a front shell left half shell, a front shell right half shell, a rear shell left half shell and a rear shell right half shell; the tail end of the left half shell of the front shell is rotatably connected with the head end of the left half shell of the rear shell; the tail end of the front shell right shell body is rotatably connected with the head end of the rear shell right shell body; the separating impulse device is arranged between the left half shell of the front shell and the right half shell of the front shell. When the revolving body flies at a high speed in dense atmosphere, the full-wrapping two-stage split separation cabin provided by the application is adopted, the pneumatic resistance moment which needs to be overcome by the separation impulse device during the first-stage split separation can be greatly reduced on the premise of not increasing the structure of the separation cabin and the complexity of the separation device, the second-stage split separation can be realized by fully utilizing the effect of incoming flow through the design of the annular cambered surface, and the reliability of the split separation of the separation cabin can be obviously improved.)

1. A full-enclosed two-stage split separation cabin for a high-speed flying rotary body in dense atmosphere is characterized by comprising:

a front housing left half shell;

a front housing right housing half;

a rear housing left half shell; the tail end of the left half shell of the front shell is rotatably connected with the head end of the left half shell of the rear shell, and the tail end of the left half shell of the rear shell is rotatably connected with the aircraft body;

a rear housing right half housing; the tail end of the front shell right shell and the head end of the rear shell right shell are rotatably connected, and the tail end of the rear shell right shell is rotatably connected with the aircraft body;

the separating impulse device is arranged between the left half shell of the front shell and the right half shell of the front shell.

2. The fully-enclosed two-stage split separation cabin for the high-speed flying rotary body in the dense atmosphere as claimed in claim 1, wherein the front shell left half shell, the front shell right half shell, the rear shell left half shell and the rear shell right half shell are in the same plane when rotating.

3. The fully-enclosed two-stage split separation cabin for the high-speed flying rotary body in the dense atmosphere as claimed in claim 1, wherein the left half shell of the rear shell and the right half shell of the rear shell have the same length, and the left half shell of the front shell and the right half shell of the front shell have the same length; the length of the left rear shell half and the right rear shell half is greater than that of the left front shell half and the right front shell half.

4. The fully-enclosed two-stage split separation cabin for the high-speed flying rotary body in the dense atmosphere as claimed in claim 1, wherein the separation impulse device is arranged close to the head ends of the left half shell and the right half shell of the front shell; the impulse direction of the separating impulse device is vertical to the length direction of the left shell body and the right shell body of the front shell body.

5. The fully-enclosed two-stage split nacelle for the high-speed flying rotor in dense atmosphere as claimed in claim 1, wherein an annular cambered surface protruding inwards is formed inside a joint of the head end of the left half shell of the rear shell and the head end of the right half shell of the rear shell.

Technical Field

The invention relates to the technical field of space vehicles, in particular to a full-packaging two-stage split separation cabin for a high-speed flight revolving body in dense atmosphere.

Background

The pod is a commonly used structure in gyrorotor aircraft. After the aircraft flies to the target area, the separation cabin completes separation and releases the mission load installed inside.

The traditional full-enclosed split separation cabin adopts a split separation scheme: the main structure of the separating cabin consists of a left half shell and a right half shell, and in the separating process, the separating impulse device provides the initial angular rate of the outward rotation of the left half shell and the right half shell around the tail rotating shaft, so that the left half shell and the right half shell are opened outwards by a small angle, and the split separation is further realized under the action of the incoming flow pneumatic force. The disadvantages are that: because the whole length of the fully-enclosed split separation cabin of the revolving body is large, the aerodynamic resistance and the moment arm acting on the outer wall of the shell of the separation cabin in the split separation process are large, when the revolving body flies in dense atmosphere at high speed, and simultaneously, because the thrust and the stroke of the separating impulse device are limited, the situation that the left half shell and the right half shell of the separation cabin are pushed away by the separating impulse device and then are instantly closed by the aerodynamic force can occur, so that the separation fails, and the fully-enclosed split separation cabin is not suitable for the split separation of the revolving body flying in dense atmosphere at high speed.

Therefore, a full-package two-stage split separation cabin for a high-speed flight revolving body in dense atmosphere needs to be developed to solve the problems.

Disclosure of Invention

The invention aims to solve the problems and designs a full-enclosed two-stage split separation cabin for a high-speed flight revolving body in dense atmosphere.

The invention realizes the purpose through the following technical scheme:

a full-enclosed two-stage split separation cabin for a high-speed flying rotary body in dense atmosphere comprises:

a front housing left half shell;

a front housing right housing half;

a rear housing left half shell; the tail end of the left half shell of the front shell is rotatably connected with the head end of the left half shell of the rear shell, and the tail end of the left half shell of the rear shell is rotatably connected with the aircraft body;

a rear housing right half housing; the tail end of the front shell right shell and the head end of the rear shell right shell are rotatably connected, and the tail end of the rear shell right shell is rotatably connected with the aircraft body;

the separating impulse device is arranged between the left half shell of the front shell and the right half shell of the front shell.

Specifically, the front shell left half shell, the front shell right half shell, the rear shell left half shell and the rear shell right half shell are in the same plane when rotating.

Further, the left rear shell half shell and the right rear shell half shell are the same in length, and the left front shell half shell and the right front shell half shell are the same in length; the length of the left rear shell half and the right rear shell half is greater than that of the left front shell half and the right front shell half.

Specifically, the setting position of the separating impulse device is close to the head ends of the left shell body and the right shell body of the front shell body; the impulse direction of the separating impulse device is vertical to the length direction of the left shell body and the right shell body of the front shell body.

Specifically, an annular cambered surface protruding inwards is formed inside the joint of the head end of the left rear shell half and the head end of the right rear shell half.

The invention has the beneficial effects that:

when the revolving body flies at a high speed in dense atmosphere, the full-wrapping two-stage split separation cabin provided by the application is adopted, the pneumatic resistance moment which needs to be overcome by the separation impulse device during the first-stage split separation can be greatly reduced on the premise of not increasing the structure of the separation cabin and the complexity of the separation device, the second-stage split separation can be realized by fully utilizing the effect of incoming flow through the design of the annular cambered surface, and the reliability of the split separation of the separation cabin can be obviously improved.

Drawings

Fig. 1 is a schematic view of a pod according to the present invention, in this case in a pre-pod separation state (partially cut away).

FIG. 2 is a schematic view of a contracting parabolic section structure of the rear shell opening of the separation cabin.

Fig. 3 is a schematic view of the pod of the present invention in which a first stage of split separation has been accomplished.

Fig. 4 is a schematic view of the pod of the present invention in which a second stage of split separation has been accomplished.

Wherein, 1-front shell left half shell; 2-a separation impulse device; 3-a front housing right half housing; 4-connecting the rotating shaft; 5-rear housing left half shell; 6-the right rear shell half; 7-annular arc surface.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "inside", "outside", "left", "right", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the present invention are conventionally placed in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is also to be noted that, unless otherwise explicitly stated or limited, the terms "disposed" and "connected" are to be interpreted broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

The following detailed description of embodiments of the invention refers to the accompanying drawings.

As shown in fig. 1, a full-enclosed two-stage split separation cabin for a high-speed flight revolving body in dense atmosphere comprises:

a front housing left half-shell 1;

a front housing right-half housing 3;

a rear housing left half shell 5; the tail end of the front shell left half shell 1 and the head end of the rear shell left half shell 5 are rotatably connected through a connecting rotating shaft 4, and the tail end of the rear shell left half shell 5 is rotatably connected with the aircraft body;

a rear housing right housing half 6; the tail end of the front shell right half shell 3 and the head end of the rear shell right half shell 6 are rotatably connected through a connecting rotating shaft 4, and the tail end of the rear shell right half shell 6 is rotatably connected with the aircraft body;

the separating impulse device 2 is arranged between the front housing left half-shell 1 and the front housing right half-shell 3.

As shown in fig. 3 and 4, the separation cabin adopts a two-stage split separation scheme, firstly, the locking of the front shell left half shell 1 and the front shell right half shell 3 is unlocked, then the separation impulse of the separation impulse device 2 acts on the front shell left half shell 1 and the front shell right half shell 3, the pneumatic resistance and the moment arm acting on the outer walls of the front shell left half shell 1 and the front shell right half shell 3 are overcome, then the front shell left half shell 1 and the front shell right half shell 3 rotate to be split and separated towards two sides, then the split separation of the rear shell left half shell 5 and the rear shell right half shell 6 is completed under the rotation pulling of the front shell left half shell 1 and the front shell right half shell 3 by using the action of the pneumatic force of incoming flow, and further, the split separation of the whole separation cabin is realized, and the task load is released.

The connecting rotating shaft 4 is arranged for guiding the relative rotating direction of the front shell relative to the rear shell in the first-stage split separation process and guiding high-speed incoming flow to the head of the rear shell through the middle of the left half shell and the right half shell of the front shell; it is defined here that the front housing left half shell 1, the front housing right half shell 3 can only be turned outwards by less than 180 °.

As shown in fig. 3 and 4, the front housing left half shell 1, the front housing right half shell 3, the rear housing left half shell 5, and the rear housing right half shell 6 are in the same plane when they rotate.

As shown in fig. 1, 3 and 4, the rear housing left half shell 5 and the rear housing right half shell 6 have the same length, and the front housing left half shell 1 and the front housing right half shell 3 have the same length; the length of the rear shell left half shell 5 and the rear shell right half shell 6 is greater than the length of the front shell left half shell 1 and the front shell right half shell 3. The structure design is favorable for reducing the pneumatic resistance acting on the outer wall of the front shell and the moment arm of the front shell relatively connected with the rotating shaft 4 when the first-stage split separation is carried out, and the reliability of the first-stage split separation is improved.

As shown in fig. 1, the separation impulse device 2 is arranged near the head ends of the front shell left half shell 1 and the front shell right half shell 3; the impulse direction of the separating impulse device 2 is perpendicular to the length direction of the left casing half and the right casing half 3 of the front casing.

As shown in fig. 2, an annular arc surface 7 protruding inwards is formed inside the joint of the head end of the left rear shell half 5 and the head end of the right rear shell half 6. The structure design is convenient for the high-speed incoming flow to enter the interior of the rear shell after the first-stage split separation.

The technical solution of the present invention is not limited to the limitations of the above specific embodiments, and all technical modifications made according to the technical solution of the present invention fall within the protection scope of the present invention.