阅读说明：本技术 一种飞行器级间连接段与助推器前封头一体化构型 (Integrated configuration of interstage connecting section of aircraft and front seal head of booster ) 是由 郭德春 朱国祥 刘晓斌 高宇驰 于 2020-11-05 设计创作，主要内容包括：本发明公开一种飞行器级间连接段与助推器前封头一体化构型,级间连接段前段的内外壁与巡航级尾段平齐,级间连接段后段的外型面与助推器前封头上的过渡外型面相切,助推器的前封头外形为横椭球,前封头内部装药。本发明采用级间连接段与助推器前封头一体化构型,助推器无前裙。前封头内部既能装药又同步承力,从而综合有利于缩减飞行器发射尺寸和质量。(The invention discloses an integrated structure of an interstage connecting section of an aircraft and a front seal head of a booster. The invention adopts an integrated structure of the interstage connecting section and the front seal head of the booster, and the booster has no front skirt. The front seal head can charge and synchronously bear force, thereby being comprehensively beneficial to reducing the launching size and the launching quality of the aircraft.)

1. The integral structure of the interstage connecting section and the front seal head of the booster of the aircraft is characterized in that the front seal head of the booster and the interstage connecting section are integrally designed.

2. The integrated configuration of the aircraft interstage connection section and the booster front end enclosure as claimed in claim 1, wherein the inner wall and the outer wall of the front section of the interstage connection section are flush with the rear section of the cruise stage, the outer profile of the rear section of the interstage connection section is tangent to the transition outer profile on the booster front end enclosure, the booster front end enclosure is in a shape of a transverse ellipsoid, and the front end enclosure is internally filled with powder.

3. The integrated configuration of the aircraft interstage connection section and the booster front head as claimed in claim 2,

the length L of the interstage connection segment is 80-200 mm;

the fillet r at the tangent position of the outer profile of the rear section of the interstage connecting section and the transition outer profile on the front seal head of the booster is 30-70 mm;

the bus of the front seal head main body of the booster is an elliptic equation, the long semi-axis of the front seal head main body is H, the short semi-axis of the front seal head main body is R, and H/R is 4/3; the relation between the short semi-axis R of the front seal head generatrix ellipse equation and the diameter D of the booster is that R is 0.5 multiplied by D;

an included angle a between a transition outer profile bus on the front seal head of the booster and a horizontal plane is 10-20 degrees, the maximum thickness h between the transition outer profile bus and the inner wall of the interstage connecting section is (1.5-2.5) × d2, and the wall thickness d2 of the cruise stage tail section is 20-60 mm.

Technical Field

The invention belongs to the technical field of aircraft appearance design, and particularly relates to a connecting structure of an interstage connecting section of an aircraft and a booster.

Background

The high-speed cruise aircraft is generally composed of a solid rocket booster (hereinafter referred to as a booster), a cruise stage and an interstage connecting section. The inter-stage connecting section is used for connecting the cruise stage and the booster in series. The conventional method of the existing aircraft is that a front skirt (see attached figure 1 in the specification, wherein 1 is a front seal head, 2 is the front skirt, and 3 is an engine body) is arranged at the front end of a booster, and then the front skirt is connected with a cruise stage through an interstage connecting section. The disadvantage of this method is that the front seal head is not filled with charge, the volume is not effectively utilized, and a separate front skirt is required to be arranged on the booster for interstage connection, so that the overall length of the aircraft is difficult to reduce, and the size and the weight scale of the aircraft are not reduced.

Disclosure of Invention

The following presents a simplified summary of the invention in order to provide a basic understanding of some aspects of the invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to determine the key or critical elements of the present invention, nor is it intended to limit the scope of the present invention. Its sole purpose is to present some concepts in a simplified form as a prelude to the more detailed description that is discussed later.

The technical problem to be solved by the invention is to provide a connecting structure of an interstage connecting section of an aircraft and a booster, which can reduce the launching size and mass of the aircraft.

The technical scheme of the invention comprises the following steps:

an integrated configuration of an interstage connecting section and a booster front end enclosure of an aircraft is provided, the aircraft is composed of a solid rocket booster, a cruise stage and the interstage connecting section, and the front end enclosure and the interstage connecting section of the booster are designed integrally.

Furthermore, the inner wall and the outer wall of the front section of the interstage connecting section are flush with the tail section of the cruise stage, the outer profile of the rear section of the interstage connecting section is tangent to the transition outer profile on the front seal head of the booster, the front seal head of the booster is in a transverse ellipsoid shape, and the inner part of the front seal head is filled with powder.

Further, the air conditioner is provided with a fan,

the length L of the interstage connection segment is 80-200 mm;

the fillet r at the tangent position of the outer profile of the rear section of the interstage connecting section and the transition outer profile on the front seal head of the booster is 30-70 mm;

the bus of the front seal head main body of the booster is an elliptic equation, the long semi-axis of the front seal head main body is H, the short semi-axis of the front seal head main body is R, and H/R is 4/3; the relation between the short semi-axis R of the front seal head generatrix ellipse equation and the diameter D of the booster is that R is 0.5 multiplied by D;

an included angle a between a transition outer profile bus on the front seal head of the booster and a horizontal plane is 10-20 degrees, the maximum thickness h between the transition outer profile bus and the inner wall of the interstage connecting section is (1.5-2.5) × d2, and the wall thickness d2 of the cruise stage tail section is 20-60 mm.

Compared with the prior art, the invention has the beneficial effects that:

the interstage connecting section and the front seal head of the booster are integrated, the booster does not have a front skirt, the front seal head is in the shape of a transverse ellipsoid, and the front seal head can be used for charging and synchronously bearing force, so that the launching size and the launching quality of an aircraft can be comprehensively reduced.

Drawings

FIG. 1 is a schematic view of a front skirt of a conventional solid rocket booster;

fig. 2 is an integrated configuration of the interstage connection section and the booster front head of the invention.

In the figure, 1 is a front seal head, 2 is a front skirt, 3 is an engine body, 4 is a cruise stage tail section, 5 is an interstage connecting section, and 6 is a booster front seal head.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

The invention adopts an integrated design structure of the rear section of the interstage connecting section and the front seal head of the booster. The inner wall and the outer wall of the front section of the interstage connecting section are flush with the cruise stage tail section, the outer profile of the rear section of the interstage connecting section is tangent to the transition outer profile on the front seal head of the booster, the front seal head of the booster is in the shape of a transverse ellipsoid, and the powder is filled in the front seal head.

In the attached figure 2, 4 is a cruise stage tail section, 5 is an interstage connecting section, and 6 is a booster front end enclosure.

d is the outer diameter of the cruise stage tail section, d1 is the inner diameter of the cruise stage tail section, d and d1 are given parameters of the design of the inter-stage connecting section, and d is 400-800 mm. d2 is the wall thickness of the cruise tail section, and d2 is usually in the range of 20-60 mm.

The length L of the interstage connecting section is 80-200 mm, and the inner wall and the outer wall of the front section of the interstage connecting section are flush with the tail section of the cruise stage. In accordance with the above table, d1 is d-2 × d2, where "x" is a multiplication in mathematics. The outer profile of the rear section of the interstage connecting section is tangent to the transition profile on the front seal head of the booster, and the fillet r is 30-70 mm.

The generatrix of the front seal head body of the booster is an elliptic equation, the major semi-axis of the main body is H, the minor semi-axis of the main body is R, H/R is 4/3, and the "/" is a division sign in mathematics. Further, the relation between the minor semi-axis R of the front seal head generatrix ellipse equation and the diameter D of the booster is that R is 0.5 XD, and the diameter D of the booster directly selects the diameter series value of domestic mature solid rocket engines, for example, D is 1000 mm.

An included angle a between a transition outer profile bus on the front seal head of the booster and a horizontal plane is 10-20 degrees, and the maximum thickness h between the transition outer profile bus and the inner wall of the interstage connecting section is (1.5-2.5) multiplied by d 2.

Compared with the prior art, the invention has the beneficial effects that:

the main advanced point of the invention is that the interstage connecting section and the front seal head of the booster are integrated, the booster has no front skirt, the front seal head is in a transverse ellipsoid shape, and the interior of the front seal head can be used for charging and synchronously bearing force, thereby being comprehensively beneficial to reducing the launching size and the launching quality of an aircraft.

The above embodiments are only for explaining and explaining the technical solution of the present invention, but should not be construed as limiting the scope of the claims. It should be clear to those skilled in the art that any simple modification or replacement based on the technical solution of the present invention may be adopted to obtain a new technical solution, which falls within the scope of the present invention.