CN112412659B - Integrated structure of interstage connecting section of aircraft and front seal head of booster - Google Patents
Integrated structure of interstage connecting section of aircraft and front seal head of booster Download PDFInfo
- Publication number
- CN112412659B CN112412659B CN202011219890.7A CN202011219890A CN112412659B CN 112412659 B CN112412659 B CN 112412659B CN 202011219890 A CN202011219890 A CN 202011219890A CN 112412659 B CN112412659 B CN 112412659B
- Authority
- CN
- China
- Prior art keywords
- booster
- seal head
- front seal
- section
- interstage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/36—Propellant charge supports
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Tires In General (AREA)
- Braking Systems And Boosters (AREA)
Abstract
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.
Description
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 that the connecting structure of the interstage connecting section of the aircraft and the booster can reduce the launching size and mass of the aircraft.
The technical scheme of the invention comprises the following steps:
the aircraft is composed of a solid rocket booster, a cruise stage and an interstage connecting section, the front end enclosure of the booster and the interstage connecting section are designed integrally, the inner wall and the outer wall of the front section of the interstage connecting section are flush with the rear 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 end enclosure of the booster, the front end enclosure of the booster is in a transverse ellipsoid shape, and the front end enclosure is internally 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 minor semi-axis R of the 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) multiplied by 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 booster front end enclosure are integrated, the booster is free of a front skirt, the front end enclosure is in the shape of a transverse ellipsoid, and the front end enclosure can be used for charging and synchronously bearing force, so that the reduction of the launching size and the launching quality of an aircraft is comprehensively facilitated.
Drawings
FIG. 1 is a schematic view of a front skirt of a conventional solid rocket booster;
fig. 2 is an integrated structure of the interstage connection section and the booster front seal 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.
Claims (1)
1. An integrated structure of an interstage connecting section of an aircraft and a booster front end enclosure is characterized in that the front end enclosure of the booster and the interstage connecting section are designed integrally; the inner wall and the outer wall of the front section of the interstage connection section are flush with the cruise stage tail section, the outer profile of the rear section of the interstage connection 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 inside of the front seal head is filled with powder;
the length L of the interstage connection section is = 80-200 mm;
the fillet r = 30-70 mm 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;
the bus of the booster front seal head main body is an elliptic equation, the major semi-axis of the booster front seal head main body is H, the minor semi-axis of the booster front seal head main body is R, and H/R = 4/3; the relation between the minor semi-axis R of the ellipse equation and the diameter D of the booster is R =0.5 × 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 = (1.5-2.5) × d2 between the transition outer profile bus and the inner wall of the interstage connecting section is larger than or equal to h = (1.5-2.5) × d2, and the wall thickness d2 of the cruise-stage tail section is = 20-60 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011219890.7A CN112412659B (en) | 2020-11-05 | 2020-11-05 | Integrated structure of interstage connecting section of aircraft and front seal head of booster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011219890.7A CN112412659B (en) | 2020-11-05 | 2020-11-05 | Integrated structure of interstage connecting section of aircraft and front seal head of booster |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112412659A CN112412659A (en) | 2021-02-26 |
| CN112412659B true CN112412659B (en) | 2021-12-10 |
Family
ID=74827961
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011219890.7A Active CN112412659B (en) | 2020-11-05 | 2020-11-05 | Integrated structure of interstage connecting section of aircraft and front seal head of booster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112412659B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412659B (en) * | 2021-12-23 | 2023-07-14 | 上海新力动力设备研究所 | Combined cone section composite shell structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4819426A (en) * | 1987-05-08 | 1989-04-11 | Morton Thiokol, Inc. | Rocket propelled vehicle forward end control method and apparatus |
| CN108801082A (en) * | 2018-04-28 | 2018-11-13 | 长沙金信诺防务技术有限公司 | A kind of the stage separation device and installation method of multistep rocket |
| CN109018445A (en) * | 2018-09-12 | 2018-12-18 | 北京航空航天大学 | Moonlet vehicle |
| CN109631688A (en) * | 2018-11-21 | 2019-04-16 | 中国运载火箭技术研究院 | A kind of X-type composite material rocket interstage section or inter-tank section connection structure |
| CN109900486A (en) * | 2019-03-04 | 2019-06-18 | 北京空天技术研究所 | A kind of winged hot aeroperformance acquisition methods of aircraft of band |
-
2020
- 2020-11-05 CN CN202011219890.7A patent/CN112412659B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4819426A (en) * | 1987-05-08 | 1989-04-11 | Morton Thiokol, Inc. | Rocket propelled vehicle forward end control method and apparatus |
| CN108801082A (en) * | 2018-04-28 | 2018-11-13 | 长沙金信诺防务技术有限公司 | A kind of the stage separation device and installation method of multistep rocket |
| CN109018445A (en) * | 2018-09-12 | 2018-12-18 | 北京航空航天大学 | Moonlet vehicle |
| CN109631688A (en) * | 2018-11-21 | 2019-04-16 | 中国运载火箭技术研究院 | A kind of X-type composite material rocket interstage section or inter-tank section connection structure |
| CN109900486A (en) * | 2019-03-04 | 2019-06-18 | 北京空天技术研究所 | A kind of winged hot aeroperformance acquisition methods of aircraft of band |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112412659A (en) | 2021-02-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2427634B1 (en) | A strut and a gas turbine structure comprising the strut | |
| CN112412659B (en) | Integrated structure of interstage connecting section of aircraft and front seal head of booster | |
| EP2492484B1 (en) | Propfan engine | |
| EP3179083A1 (en) | Asymmetric exhaust nozzle for gas turbine engine | |
| CN201983920U (en) | Segmentation jet tube for supersonic wind tunnel | |
| CN113006940B (en) | Micro turboprop engine without external speed reducer | |
| CN109763916A (en) | A kind of solid rocket motor nozzle component connection sealing structure | |
| CN109470089B (en) | Small-size bullet wing structure of short beam core | |
| CN101576021A (en) | Spiral type thrust engine | |
| EP1988274A2 (en) | Turbojet engine | |
| CN207664795U (en) | A kind of New energy automobile motor hollow rotating shaft | |
| EP3557035A1 (en) | Turbofan engine | |
| EP2372109A2 (en) | Diffusive nacelle | |
| CN214366867U (en) | Sealing structure of non-notch sealing ring and turbocharger | |
| CN210416996U (en) | Lip and intake duct butt-joint structural | |
| CN113123876A (en) | Aircraft engine without turbine rear case structure | |
| CN219345075U (en) | Compressor shell for engine | |
| CN111661344A (en) | Wing-body integrated aircraft propulsion system | |
| CN111774512A (en) | Method for manufacturing integral heavy-load bearing structure pull rod based on volume forming | |
| CN204438928U (en) | A kind of civil rocket bullet monoblock type projectile tail | |
| CN217751236U (en) | Assembly fixture for aviation air conduit front neck elastic energy storage sealing ring | |
| CN219035969U (en) | Emergency repair device for natural gas pipeline | |
| CN220865664U (en) | Double-layer oil tank gas circuit connecting device | |
| CN217583121U (en) | Two-in-one motor drive assembly capable of reducing axial dimension | |
| CN207363761U (en) | A kind of pressure shell air inlet sound insulation board mounting structure for turbocharger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |