CN104015926A - Implication type cover hood abandoning scheme for hypersonic aircraft - Google Patents
Implication type cover hood abandoning scheme for hypersonic aircraft Download PDFInfo
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- CN104015926A CN104015926A CN201410201820.7A CN201410201820A CN104015926A CN 104015926 A CN104015926 A CN 104015926A CN 201410201820 A CN201410201820 A CN 201410201820A CN 104015926 A CN104015926 A CN 104015926A
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Abstract
The invention discloses an implication type cover hood abandoning scheme for a hypersonic aircraft, and belongs to the technical field of aerodynamic designing of hypersonic aircrafts. In the abandoning scheme, an aircraft body, a cover hood body and a baffle are adopted, the cover hood body is fixed on the aircraft body, and the baffle is fixed on the cover hood body; with regard to abandoning a cover hood, firstly, the baffle is opened by a certain angle through an explosive bolt, and then the whole cover hood comprising the cover hood body and the baffle are stripped from the aircraft body through aerodynamic force. According to the implication type cover hood abandoning scheme for the hypersonic aircraft, the cover hood can be quickly stripped from the hypersonic aircraft so that air can smoothly enter the aircraft.
Description
Technical field
The present invention relates to a kind of hypersonic aircraft " connection formula " calotte and abandon scheme, belong to hypersonic aircraft pneumatic design field.
Background technology
Hypersonic aircraft generally refers to that flying speed exceedes the aircraft of Mach 5.0.Hypersonic aircraft can be realized the imagination of " beating for 1 hour all over the whole world ".Realizing one of gordian technique of hypersonic flight is exactly engine installation.Also cannot accomplish, by single airbreathing motor, aircraft is accelerated to hypersonic flight state by quiescence with current technical merit.For the problem of engine installation, main solution thinking is to adopt combination engine both at home and abroad, comprise turbine base combination circulation (Turbine Based Combined Cycle, TBCC) and rocket based combined cycle (Rocket Based Combined Cycle, RBCC).
Wherein TBCC driving engine is because technical risk is higher, also also do not have at present TBCC driving engine to apply on hypersonic aircraft both at home and abroad, and RBCC driving engine is Comparatively speaking comparatively simple, can first adopt the power of RBCC driving engine as hypersonic aircraft, launch the flight test of aircraft aerodynamic configuration.The principle of work of RBCC driving engine is first to adopt rocket engine that hypersonic aircraft is accelerated to Ma4～5 in aircraft, and then rocket engine quits work, and the punching press/scramjet engine of hypersonic aircraft inside is started working.In order to protect internal flow channel, ensure by rocket booster to punching press/scramjet engine transient process intake duct starting memory reduce hypersonic aircraft propelling resistance, at one section of calotte of hypersonic aircraft inlet mouth section design.Calotte in the time that rocket booster quits work, need to peel off from aircraft, thereby make air enter punching press/scramjet engine.
Summary of the invention
For the calotte that makes hypersonic aircraft can depart from aircraft to punching press/scramjet engine work transient process in rocket engine work, " the connection formula " that the invention provides a kind of calotte abandons scheme, and this scheme can be peeled off calotte from hypersonic aircraft smoothly.
The technical solution adopted for the present invention to solve the technical problems is: " connection formula " calotte abandon scheme for aircraft be the hypersonic aircraft similar with X43.Therefore basic aerodynamic configuration and the X43 of aircraft are similar, and the configuration design of calotte needs and the profile of aircraft matches.The basic ideas of calotte configuration design are the effects that will play protection internal flow channel and reduce flight resistance.
" connection formula " calotte is abandoned the mentality of designing of scheme:
One, calotte is abandoned opportunity
Abandoning of calotte need to be carried out on suitable opportunity, otherwise will likely cause the inoperative of inlet channel, abandoned calotte after selecting aircraft to separate with rocket booster by analysis.
Two, one-sided peel-open separates
Satellite launch arrives after certain altitude, and abandoning the scheme that fairing adopts is to separate to both sides strip off, and the separation of hypersonic aircraft calotte adopts one-sided separation, separates to the below of aircraft.
Three, connection formula is abandoned scheme
The scheme of abandoning of so-called connection formula calotte, while being calotte design, be divided into two parts calotte main body and baffle plate, baffle plate adopts explosive bolt to be connected with calotte main body, explosive bolt is by baffle plate from calotte body portion from deflecting down certain angle, and gas enters aircraft inside and under Aerodynamic force action, whole calotte peeled off from aircraft surface.Wherein be rectangle shape with sweepback sidewall of baffle plate, the design of sweepback sidewall is the Joint strenght in order to increase baffle plate and calotte main body, reduces both sides overflow simultaneously, thereby be convenient to set up larger pressure reduction, calotte main body is separated from aircraft.
The invention has the beneficial effects as follows, rapidly calotte is peeled off from hypersonic aircraft, make gas enter smoothly aircraft inside.
Brief description of the drawings
Fig. 1 is the lateral plan that hypersonic aircraft adds calotte.
Fig. 2 is the upward view that hypersonic aircraft adds calotte.
Fig. 3-7th, " connection formula " calotte is abandoned process.
1. hypersonic aircraft 2. calotte main body 3. baffle plates in figure; 30-sweepback sidewall.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described.
Fig. 1,2 has shown that hypersonic aircraft adds lateral plan and the upward view of calotte.The process that hypersonic aircraft " connection formula " calotte is abandoned has been illustrated in Fig. 3-7, Fig. 3 is that calotte is fixed on the situation on hypersonic aircraft, Fig. 4 is that baffle plate is opened rear residing position by explosive bolt, Fig. 5 is for to lead whole calotte from hypersonic aircraft at Aerodynamic force action lower baffle plate, Fig. 6 and Fig. 7 show calotte after abandoning with the relative position of aircraft.
" the connection formula " of hypersonic aircraft calotte of the present invention abandons scheme, comprise aircraft body 1 and calotte, calotte comprises calotte main body 2 and baffle plate 3, and calotte main body 2 is fixed in aircraft body 1, baffle plate 3 is fixed in calotte main body 2 by explosive bolt, and wherein scheme comprises the steps:
1). by explosive bolt, baffle plate 3 is deflected down to separation certain angle from calotte main body 2;
2). gas enters hypersonic aircraft 1 inside;
3). Aerodynamic force action is in baffle plate 3 and calotte main body 2 and then calotte is abandoned from aircraft body 1.
The above is only the preferred embodiment of the present invention, it should be pointed out that for those skilled in the art, can also make under the premise without departing from the principles of the invention some improvement, and these improve and also should be considered as protection scope of the present invention.
Claims (3)
1. " the connection formula " of a hypersonic aircraft calotte abandons scheme, comprise aircraft body (1) and calotte, described calotte comprises calotte main body (2) and baffle plate (3), described calotte main body (2) is fixed in aircraft body (1), it is upper that baffle plate (3) is fixed on calotte main body (2) by explosive bolt, it is characterized in that: described scheme comprises the steps:
1). by explosive bolt, baffle plate (3) is deflected down to separation certain angle from calotte main body (2);
2). gas enters hypersonic aircraft (1) inside;
3). Aerodynamic force action is in baffle plate (3) and calotte main body (2) and then calotte is abandoned from aircraft body (1).
2. " the connection formula " of hypersonic aircraft calotte as claimed in claim 1 abandons scheme, it is characterized in that: described baffle plate (3) comprises increasing the sweepback sidewall (30) of baffle plate (3) and calotte main body (2) Joint strenght.
3. " the connection formula " of hypersonic aircraft calotte as claimed in claim 1 abandons scheme, it is characterized in that: abandoning of described calotte separates the one-sided separation of employing, separates to the below of aircraft body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410201820.7A CN104015926B (en) | 2014-05-13 | 2014-05-13 | Scheme abandoned by hypersonic aircraft connection formula calotte |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410201820.7A CN104015926B (en) | 2014-05-13 | 2014-05-13 | Scheme abandoned by hypersonic aircraft connection formula calotte |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104015926A true CN104015926A (en) | 2014-09-03 |
| CN104015926B CN104015926B (en) | 2017-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410201820.7A Active CN104015926B (en) | 2014-05-13 | 2014-05-13 | Scheme abandoned by hypersonic aircraft connection formula calotte |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108110434A (en) * | 2017-12-16 | 2018-06-01 | 贵州航天电子科技有限公司 | A kind of answer signal decay cover |
| CN110749250A (en) * | 2019-10-30 | 2020-02-04 | 中国科学院力学研究所 | Novel hypersonic aircraft safety cover |
| CN111516871A (en) * | 2020-04-30 | 2020-08-11 | 浙江大学 | Supersonic stealth unmanned aerial vehicle with pneumatic stealth integrated design |
| CN113247277A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Hypersonic air inlet duct conformal fairing scheme with folding wings |
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| US6193187B1 (en) * | 1998-12-31 | 2001-02-27 | Harry Scott | Payload carry and launch system |
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
| CN102705081A (en) * | 2012-05-23 | 2012-10-03 | 南京航空航天大学 | Binary hypersonic variable geometrical inlet channel, design method and work mode |
| CN202628279U (en) * | 2012-05-23 | 2012-12-26 | 南京航空航天大学 | Binary hypersonic speed-variable geometric air inlet channel |
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2014
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6193187B1 (en) * | 1998-12-31 | 2001-02-27 | Harry Scott | Payload carry and launch system |
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
| CN102705081A (en) * | 2012-05-23 | 2012-10-03 | 南京航空航天大学 | Binary hypersonic variable geometrical inlet channel, design method and work mode |
| CN202628279U (en) * | 2012-05-23 | 2012-12-26 | 南京航空航天大学 | Binary hypersonic speed-variable geometric air inlet channel |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108110434A (en) * | 2017-12-16 | 2018-06-01 | 贵州航天电子科技有限公司 | A kind of answer signal decay cover |
| CN110749250A (en) * | 2019-10-30 | 2020-02-04 | 中国科学院力学研究所 | Novel hypersonic aircraft safety cover |
| CN111516871A (en) * | 2020-04-30 | 2020-08-11 | 浙江大学 | Supersonic stealth unmanned aerial vehicle with pneumatic stealth integrated design |
| CN113247277A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Hypersonic air inlet duct conformal fairing scheme with folding wings |
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| Publication number | Publication date |
|---|---|
| CN104015926B (en) | 2017-01-04 |
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Effective date of registration: 20180409 Address after: Yudaojie Qinhuai District of Nanjing City, Jiangsu Province, No. 29 210016 Co-patentee after: Beijing Institute of Power Machinery Patentee after: Nanjing University of Aeronautics and Astronautics Address before: Yudaojie Qinhuai District of Nanjing City, Jiangsu Province, No. 29 210016 Patentee before: Nanjing University of Aeronautics and Astronautics |
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