CN102941927A - Axial-symmetry blunt body returner - Google Patents
Axial-symmetry blunt body returner Download PDFInfo
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- CN102941927A CN102941927A CN2012105200170A CN201210520017A CN102941927A CN 102941927 A CN102941927 A CN 102941927A CN 2012105200170 A CN2012105200170 A CN 2012105200170A CN 201210520017 A CN201210520017 A CN 201210520017A CN 102941927 A CN102941927 A CN 102941927A
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- auricle
- cabin
- recoverable capsule
- returner
- blunt
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Abstract
The invention discloses an axial-symmetry blunt body returner. The returner consists of a cabin body (1), a lug (2) and a pair of edge strips (3), wherein the lug (2) is positioned at the center of a windward surface of the tail of the cabin body (1); and the edge strips (3) are positioned on the left side and the right side of the cabin body (1). The edge strips are used for changing the structure of a flow field of a leeside of the returner at subsonic speed, so that the pitching torque which makes the returner unstable is reduced; and the lug is used for producing the pitching torque favorable for the stability of the returner. The appearance of the returner can meet the requirement on a lift-drag ratio of human lunar exploration; and single-point stabilization can be realized.
Description
Technical field
The present invention relates to a kind of recoverable capsule aerodynamic arrangement, can be applicable to subsonic velocity, transonic speed, supersonic speed and Hypersonic reentry flight.
Background technology
When manned moon landing's recoverable capsule returns ground, need to reenter flight with the second cosmic velocity, reenter flight to compare difficulty larger with the first cosmic velocity is manned, therefore higher to the requirement of recoverable capsule (generally adopting rotational symmetry blunt body profile) aerodynamic characteristic.The Shenzhou manned spacecraft recoverable capsule of China has realized that successfully the manned of the first cosmic velocity reenters flight, but this recoverable capsule aerodynamic configuration can not satisfy the manned requirement that reenters of the second cosmic velocity, and one of them important reason is that 1ift-drag ratio is on the low side.The manned 1ift-drag ratio that reenters the General Requirements recoverable capsule of the second cosmic velocity is more than 0.30, and the 1ift-drag ratio of Shenzhou recoverable capsule only has about 0.25.Such as Apollo, often there is the stable problem of non-single-point in the recoverable capsule profile that 1ift-drag ratio is higher, namely has two or more static-stability trim points in 0 °～180 ° angle of attack scopes.If with non-design trim ang1e of attack flight, thermal protection system can not provide enough protections to recoverable capsule so in reentering process, its consequence will be catastrophic.Apollo has adopted cover Reaction control system (RCS) for subsequent use to guarantee still can control the flight attitude of recoverable capsule in the situation that master control unit loses efficacy.But under the situation that control system all lost efficacy, the flight safety of recoverable capsule is difficult to be guaranteed.And for the stable recoverable capsule profile of single-point, such as Shenzhou, even control system lost efficacy, recoverable capsule is in the situation that flight attitude off-design point can be got back to unique static-stability trim design point automatically.
As shown in Figure 1, the configuration design of Shenzhou recoverable capsule realizes that by increase a pair of stable auricle at rear body single-point is stable, if remove this two auricles, Shenzhou recoverable capsule profile is that non-single-point is stable.But this auricle design is more limited for the efficient of improving recoverable capsule single-point stability characteristic (quality), satisfy the manned requirement that reenters flight of the second cosmic velocity if increase the rear body reversed cone angle of Shenzhou recoverable capsule profile to improve its 1ift-drag ratio, adopt so same auricle design can not make new profile realize that single-point is stable.
Therefore, how can obtain 1ift-drag ratio higher, have again the recoverable capsule profile of single-point stability characteristic (quality) simultaneously, be a technical barrier of manned moon landing's recoverable capsule aerodynamic arrangement design.
Summary of the invention
Technical matters to be solved by this invention is to overcome the deficiencies in the prior art, provides a kind of 1ift-drag ratio higher, the rotational symmetry blunt body recoverable capsule that has again the single-point stability characteristic (quality) simultaneously.
Technical scheme of the present invention is: a kind of rotational symmetry blunt body recoverable capsule comprises a cabin body, an auricle and two edge strips; Described cabin body is the rotational symmetry blunt body, is comprised of head, rounding, rear body, spherical transition body and afterbody successively; Described head is the spherical crown shape, and described head transits to rear body by rounding, and rear body is conical surface shape; Described afterbody is cone or cylinder, is connected by the spherical transition body between rear body and the afterbody; Described auricle is installed in the central authorities of the windward side of described spherical transition body, and two edge strips lay respectively at the left and right sides of cabin body.
The outer rim of edge strip is shaped as straight line or curve.
The thickness of the Thickness Ratio auricle trailing edge of auricle and body junction, cabin is large.
The width of the Width trailing edge of auricle and body junction, cabin is little.
The auricle upper and lower surface is cambered surface, and auricle one end is installed near near the bottom of spherical transition body, and the auricle other end extends to concordant with the bottom of cabin body.
The present invention's advantage compared with prior art is as follows:
(1) the present invention adopts the design of single auricle being installed in both sides installation edge strip and the part that the rear body that is connected is connected with afterbody, the flow field structure of recoverable capsule lee face when wherein edge strip can change subsonic velocity, reduce so that the unsettled pitching moment of recoverable capsule, auricle can produce and be conducive to the stable pitching moment of recoverable capsule.Compare with the design of existing ears sheet, the improvement effect of recoverable capsule single-point stability characteristic (quality) is improved greatly.
(2) 1ift-drag ratio of recoverable capsule of the present invention can reach more than 0.30; Can solve simultaneously the manned moon landing and reenter needs of problems to recoverable capsule 1ift-drag ratio and single-point stability, and prior art can not.
(3) the present invention is simple in structure, easily realizes.
Description of drawings
Fig. 1 is the schematic three dimensional views of the recoverable capsule of existing ears sheet profile.
Fig. 2 is recoverable capsule of the present invention cabin body profile figure.
Fig. 3 is recoverable capsule three-dimensional profile figure of the present invention.
Fig. 4 a-Fig. 4 c is the edge strip profile schematic diagram of difformity, size.
Fig. 5 is the first auricle structural representation, and wherein Fig. 5 a is that lateral plan, Fig. 5 b are birds-eye view.
Fig. 6 is the second auricle structural representation, and wherein Fig. 6 a is that lateral plan, Fig. 6 b are birds-eye view.
Fig. 7 is the third auricle structural representation, and wherein Fig. 7 a is that lateral plan, Fig. 7 b are birds-eye view.
Fig. 8 is the comparison diagram of cabin body profile, ears sheet profile and profile single-point stability characteristic (quality) of the present invention.
Fig. 9 is the comparison diagram of cabin body profile, ears sheet profile and profile 1ift-drag ratio characteristic of the present invention.
The specific embodiment
Below in conjunction with example, the specific embodiment of the present invention is described.
As shown in Figure 3, rotational symmetry blunt body recoverable capsule of the present invention comprises a cabin body 1, an auricle 2 and two edge strips 3.Described auricle 2 is installed in the central authorities of windward side of the spherical transition body of cabin body 1, and two edge strips 3 lay respectively at the left and right sides of cabin body 1.
The below is introduced the method for designing of each parts:
1. according to overall dimension and 1ift-drag ratio requirement, generate recoverable capsule cabin body profile.The cabin body profile is the spherical crown back taper, as shown in Figure 2.Cabin body head 11 is the spherical crown shape, is the rear body 13 of conical surface shape by rounding 12 transition, and afterbody 15 is cone or cylinder, is connected by spherical transition body 14 between rear body 13 and the afterbody 15.The maximum cross-section diameter d of cabin body
mBe the principal parameter that determines the recoverable capsule size, determine according to total demand; Radius of spherical crown R
NWith reversed cone angle θ be the main geometric parameters that affects the recoverable capsule 1ift-drag ratio.Radius of spherical crown R
NValue is generally at 1.0 times to 1.2 times d
mBetween, reversed cone angle θ value is generally between 7 °～33 °.
2. each side generate an edge strip at the cabin body, the size and dimension of edge strip can be done suitable adjustment according to the actual requirements, shown in Fig. 4 a-c.The outer rim of edge strip is shaped as straight line or curve.Edge strip shown in Fig. 4 a, its outer rim is shaped as curve, and its height and thickness are respectively body maximum cross-section, cabin diameter d
m5% and 2.5%.Edge strip shown in Fig. 4 b, its outer rim is shaped as curve, and the height of its aspect ratio Fig. 4 a is little.Shown in Fig. 4 c, change edge strip outer rim shape into straight line.
3. generate an auricle in the windward side at body rear portion, cabin central authorities, the size of auricle, shape and installation site also can appropriately adjust according to actual needs, shown in Fig. 5-7.Auricle and body junction, cabin are thicker, and trailing edge is then thinner.Auricle upper and lower surface shown in Figure 5 is cambered surface, and auricle one end is installed near near the bottom of spherical transition body, and the auricle other end extends to concordant with the bottom of cabin body; The width of the Width trailing edge of auricle and body junction, cabin is little; Auricle width average and length are respectively body maximum cross-section, cabin diameter d
m25% and 17%.As shown in Figure 6, the upper and lower surface of auricle is the plane, and it is installed near near the top of spherical transition body.As shown in Figure 7, the upper and lower surface of auricle is the plane, and it is installed near near the bottom of spherical transition body.
The Main Function of edge strip is the flow field structure of recoverable capsule lee face when changing subsonic velocity, reduces so that the unsettled pitching moment of recoverable capsule, and the Main Function of auricle is to produce to be conducive to the stable pitching moment of recoverable capsule.
Suppose to adopt the recoverable capsule profile and the profile that does not adopt profile of the present invention (only cabin body) and adopt existing ears sheet design of the present invention's design, the cabin body of these three profiles is on all four.The R of cabin body profile
NBe respectively 1.2 times of d with the θ value
mWith 16 °.
Fig. 8 has provided these three profiles when Mach number Ma=0.6, relatively the pitching moment coefficient C of barycenter
MzComparison with the angle of attack change curve.If C
Mz～α curve only has a static-stability trim point (at this C in ° scope of α=0～-180
Mz=0 and C
MzDerivative C to α
Mz a＜0), then this profile is that single-point is stable, otherwise is that non-single-point is stable.As seen from Figure 6, former cabin body profile is that non-single-point is stable, adopts design of the present invention to realize that single-point is stable afterwards, adopts existing ears sheet design can not realize that then single-point is stable.
Fig. 9 has provided these three profiles when Mach number Ma=10, and 1ift-drag ratio L/D is with the comparison of angle of attack change curve.As seen from the figure, adopt design of the present invention little on the impact of recoverable capsule 1ift-drag ratio.
Claims (5)
1. a rotational symmetry blunt body recoverable capsule is characterised in that: comprise a cabin body (1), an auricle (2) and two edge strips (3); Described cabin body is the rotational symmetry blunt body, is comprised of head (11), rounding (12), rear body (13), spherical transition body (14) and afterbody (15) successively; Described head (11) is the spherical crown shape, and described head (11) transits to rear body (13) by rounding (12), and rear body (13) is conical surface shape; Described afterbody (15) is cone or cylinder, is connected by spherical transition body (14) between rear body (13) and the afterbody (15); Described auricle (2) is installed in the central authorities of the windward side of described spherical transition body (14), and two edge strips 3 lay respectively at the left and right sides of cabin body (1).
2. a kind of rotational symmetry blunt body recoverable capsule according to claim 1, be characterised in that: the outer rim of edge strip is shaped as straight line or curve.
3. a kind of rotational symmetry blunt body recoverable capsule according to claim 1, be characterised in that: the thickness of the Thickness Ratio auricle trailing edge of auricle and body junction, cabin is large.
4. a kind of rotational symmetry blunt body recoverable capsule according to claim 1, be characterised in that: the width of the Width trailing edge of auricle and body junction, cabin is little.
5. according to claim 3 or 4 described a kind of rotational symmetry blunt body recoverable capsules, be characterised in that: the auricle upper and lower surface is cambered surface, auricle one end is installed near near the bottom of spherical transition body (14), and the auricle other end extends to concordant with the bottom of cabin body.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210520017.0A CN102941927B (en) | 2012-11-30 | 2012-11-30 | Axial-symmetry blunt body returner |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210520017.0A CN102941927B (en) | 2012-11-30 | 2012-11-30 | Axial-symmetry blunt body returner |
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| CN102941927A true CN102941927A (en) | 2013-02-27 |
| CN102941927B CN102941927B (en) | 2015-06-17 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103910067A (en) * | 2013-11-21 | 2014-07-09 | 芜湖长启炉业有限公司 | Composite energy absorption foaming aluminum base of spacecraft recovery cover |
| CN113734473A (en) * | 2021-08-31 | 2021-12-03 | 北京空间飞行器总体设计部 | Pneumatic layout of high-speed-reduction extraterrestrial celestial body entering device with rear body resistance and stability increasing function |
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| CN1978279A (en) * | 2005-12-05 | 2007-06-13 | 罗进南 | Efficient flying boat and missile with tail-wing-skirt self-stabilizing return capsule |
| CN101112915A (en) * | 2006-07-25 | 2008-01-30 | 徐亮良 | Aerospace craft return retarding apparatus |
| CN101910002A (en) * | 2007-11-29 | 2010-12-08 | 阿斯特里姆有限公司 | Spacecraft afterbody device |
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2012
- 2012-11-30 CN CN201210520017.0A patent/CN102941927B/en active Active
Patent Citations (3)
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| CN1978279A (en) * | 2005-12-05 | 2007-06-13 | 罗进南 | Efficient flying boat and missile with tail-wing-skirt self-stabilizing return capsule |
| CN101112915A (en) * | 2006-07-25 | 2008-01-30 | 徐亮良 | Aerospace craft return retarding apparatus |
| CN101910002A (en) * | 2007-11-29 | 2010-12-08 | 阿斯特里姆有限公司 | Spacecraft afterbody device |
Non-Patent Citations (3)
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| 方方: "《全国低跨超声速空气动力学文集（2001）》", 1 October 2001, article "飞船返回舱多个配平攻角解决方案" * |
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| 陈冰雁; 詹慧玲; 周伟江; 刘周: "改善再入返回器稳定特性的气动设计研究", 《中国宇航学会深空探测技术专业委员会第九届学术年会论文集（上册）》, 17 October 2012 (2012-10-17), pages 160 - 161 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103910067A (en) * | 2013-11-21 | 2014-07-09 | 芜湖长启炉业有限公司 | Composite energy absorption foaming aluminum base of spacecraft recovery cover |
| CN113734473A (en) * | 2021-08-31 | 2021-12-03 | 北京空间飞行器总体设计部 | Pneumatic layout of high-speed-reduction extraterrestrial celestial body entering device with rear body resistance and stability increasing function |
| CN113734473B (en) * | 2021-08-31 | 2022-10-14 | 北京空间飞行器总体设计部 | Pneumatic layout of high-speed-reduction extraterrestrial celestial body entering device with rear body resistance and stability increasing function |
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| CN102941927B (en) | 2015-06-17 |
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