CN102941927B - Axial-symmetry blunt body returner - Google Patents
Axial-symmetry blunt body returner Download PDFInfo
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- CN102941927B CN102941927B CN201210520017.0A CN201210520017A CN102941927B CN 102941927 B CN102941927 B CN 102941927B CN 201210520017 A CN201210520017 A CN 201210520017A CN 102941927 B CN102941927 B CN 102941927B
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- auricle
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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 to ground, need with second cosmic velocity ablated configuration, compare difficulty with the manned ablated configuration of the first cosmic velocity larger, therefore higher to the requirement of recoverable capsule (general employing rotational symmetry blunt body profile) aerodynamic characteristic.The Shenzhou manned spacecraft recoverable capsule of China successfully achieves the manned ablated configuration of the first cosmic velocity, but this recoverable capsule aerodynamic configuration can not meet the manned requirement reentered of the second cosmic velocity, and one of them important reason is that 1ift-drag ratio is on the low side.The second cosmic velocity is manned reenters the 1ift-drag ratio of General Requirements recoverable capsule more than 0.30, and the 1ift-drag ratio of Shenzhou recoverable capsule only has about 0.25., as Apollo, often there is the problem that non-single-point is stable in the recoverable capsule profile that 1ift-drag ratio is higher, namely in 0 ° ~ 180 ° range of angles of attack, there is two or more static-stability trim point.If recoverable capsule is reentering with non-design trim ang1e of attack flight in process, so thermal protection system can not provide enough protections, and its consequence will be catastrophic.Apollo have employed the flight attitude that a set of Reaction control system for subsequent use (RCS) guarantees still can control when master control unit lost efficacy recoverable capsule.But when control system all lost efficacy, the flight safety of recoverable capsule was difficult to be guaranteed.And for the stable recoverable capsule profile of single-point, as Shenzhou, even if control system lost efficacy, recoverable capsule can automatically return to unique static-stability trim design point when flight attitude off-design point.
As shown in Figure 1, the configuration design of Shenzhou recoverable capsule is stablized auricle for a pair by increasing at rear body to realize single-point stable, if remove this two auricles, Shenzhou recoverable capsule profile is that non-single-point is stable.But this auricle design is limited for the efficiency comparison improving recoverable capsule single-point stability characteristic (quality), if the rear body reversed cone angle increasing Shenzhou recoverable capsule profile is to improve its 1ift-drag ratio to meet the requirement of the manned ablated configuration of the second cosmic velocity, so adopts same auricle design that new profile can not be made to realize single-point and stablize.
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 overcomes the deficiencies in the prior art, provides a kind of 1ift-drag ratio higher, has again the Axial-symmetry blunt body returner of single-point stability characteristic (quality) simultaneously.
Technical scheme of the present invention is: a kind of Axial-symmetry blunt body returner, comprises a cabin body, an auricle and two edge strips; Described cabin body is rotational symmetry blunt body, is made up of successively head, rounding, rear body, spherical transition body and afterbody; Described head is spherical cap shape, and described head transits to rear body by rounding, and rear body is conical surface shape; Described afterbody is cone or cylinder, and rear body is connected by spherical transition body with between afterbody; Described auricle is arranged on 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 shape of edge strip is straight line or curve.
The thickness of the Thickness Ratio auricle trailing edge of auricle and body junction, cabin is large.
Auricle is less than the width of trailing edge with the width of body junction, cabin.
Auricle upper and lower surface is cambered surface, and auricle one end is arranged 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 is compared with prior art as follows:
(1) the present invention adopts the design of installing single auricle in both sides installation edge strip and the part be connected with afterbody at rear body, the flow field structure of recoverable capsule lee face when wherein edge strip can change subsonic velocity, reduce the pitching moment making recoverable capsule instability, auricle can produce and be conducive to the stable pitching moment of recoverable capsule.Compared with designing with existing ears sheet, the improvement result 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 manned moon landing simultaneously and reenter needs of problems to recoverable capsule 1ift-drag ratio and single-point stability, and prior art can not.
(3) structure of the present invention is simple, easily realizes.
Accompanying drawing explanation
Fig. 1 is the schematic three dimensional views of the recoverable capsule of existing ears sheet profile.
Fig. 2 is recoverable capsule cabin body profile figure of the present invention.
Fig. 3 is recoverable capsule three-dimensional profile figure of the present invention.
Fig. 4 a-Fig. 4 c is the edge strip appearance schematic diagram of difformity, size.
Fig. 5 is the first auricle structural representation, and wherein Fig. 5 a is lateral plan, Fig. 5 b is birds-eye view.
Fig. 6 is the second auricle structural representation, and wherein Fig. 6 a is lateral plan, Fig. 6 b is birds-eye view.
Fig. 7 is the third auricle structural representation, and wherein Fig. 7 a is lateral plan, Fig. 7 b is 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.
Detailed description of the invention
Below in conjunction with example, the specific embodiment of the present invention is described.
As shown in Figure 3, Axial-symmetry blunt body returner of the present invention comprises a cabin body 1, auricle 2 and two edge strips 3.Described auricle 2 is arranged on the central authorities of the 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.
Below the method for designing of each parts is introduced:
1., according to overall dimension and 1ift-drag ratio requirement, generate recoverable capsule cabin body profile.Cabin body profile is spherical crown back taper, as shown in Figure 2.Cabin body head 11 is spherical cap shape, and be the rear body 13 of conical surface shape by rounding 12 transition, afterbody 15 is cone or cylinder, and rear body 13 is connected by spherical transition body 14 with between afterbody 15.The maximum cross-section diameter d of cabin body
mbe the principal parameter determining recoverable capsule size, determine according to total demand; Radius of spherical crown R
nthe main geometric parameters affecting recoverable capsule 1ift-drag ratio with reversed cone angle θ.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 cabin body, the size and dimension of edge strip can do suitable adjustment according to the actual requirements, as shown in figures 4 a-c.The outer rim shape of edge strip is straight line or curve.Edge strip as shown in fig. 4 a, its outer rim shape is curve, and its height and thickness are respectively body maximum cross-section, cabin diameter d
m5% and 2.5%.Edge strip as shown in Figure 4 b, its outer rim shape is curve, and the height of its aspect ratio Fig. 4 a is little.As illustrated in fig. 4 c, edge strip outer rim shape is changed into straight line.
3. generate an auricle in the windward side central authorities at body rear portion, cabin, the size of auricle, shape and installation site also can appropriately adjust according to actual needs, as illustrated in figs. 5-7.Auricle and body junction, cabin thicker, trailing edge is then thinner.The upper and lower surface of auricle shown in Fig. 5 is cambered surface, and auricle one end is arranged near the bottom of spherical transition body, and the auricle other end extends to concordant with the bottom of cabin body; Auricle is less than the width of trailing edge with the width of body junction, cabin; 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 plane, and it is arranged on the near top near spherical transition body.As shown in Figure 7, the upper and lower surface of auricle is plane, and it is arranged 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 the pitching moment making recoverable capsule instability, and the Main Function of auricle produces to be conducive to the stable pitching moment of recoverable capsule.
Suppose to adopt the recoverable capsule profile of the present invention's design and the profile not adopting profile of the present invention (only cabin body) and adopt existing ears sheet to design, the cabin body of these three profiles is on all four.The R of cabin body profile
n1.2 times of d are respectively with θ value
mwith 16 °.
Fig. 8 gives these three profiles when Mach number Ma=0.6, the pitching moment coefficient C of relative barycenter
mzwith the comparison of angle of attack change curve.If C
mz~ α curve only has a static-stability trim point (at this C within the scope of α=0 ~-180 °
mz=0 and C
mzto the derivative C of 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, achieves single-point and stablize after adopting design of the present invention, adopts the design of existing ears sheet then can not realize single-point and stablizes.
Fig. 9 gives 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 the impact of design of the present invention on recoverable capsule 1ift-drag ratio little.
Claims (4)
1. an Axial-symmetry blunt body returner, this Axial-symmetry blunt body returner, with second cosmic velocity ablated configuration, is characterised in that: comprise a cabin body (1), an auricle (2) and two edge strips (3); Described cabin body is rotational symmetry blunt body, is made up of successively head (11), rounding (12), rear body (13), spherical transition body (14) and afterbody (15); Described head (11) is spherical cap 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 between rear body (13) with afterbody (15) by spherical transition body (14); Described auricle (2) is arranged on 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); The outer rim shape of edge strip (3) is curve, and its height and thickness are respectively body maximum cross-section, cabin diameter d
m5% and 2.5%.
2. a kind of Axial-symmetry blunt body returner according to claim 1, is characterised in that: the thickness of the Thickness Ratio auricle trailing edge of auricle and body junction, cabin is large.
3. a kind of Axial-symmetry blunt body returner according to claim 1, is characterised in that: auricle is less than the width of trailing edge with the width of body junction, cabin.
4. a kind of Axial-symmetry blunt body returner according to Claims 2 or 3, be characterised in that: auricle upper and lower surface is cambered surface, auricle one end is arranged 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 CN102941927A (en) | 2013-02-27 |
| CN102941927B true CN102941927B (en) | 2015-06-17 |
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| CN201210520017.0A Active CN102941927B (en) | 2012-11-30 | 2012-11-30 | Axial-symmetry blunt body returner |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 |
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 |
-
2012
- 2012-11-30 CN CN201210520017.0A patent/CN102941927B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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)
| Title |
|---|
| 方方.飞船返回舱多个配平攻角解决方案.《全国低跨超声速空气动力学文集(2001)》.2001,第一卷全文. * |
| 航天飞机在再入段的亚音速空气动力特性的一种有效算法;王良益;《南京航空学院院报》;19900630;第22卷(第2期);第37、39、 40页、图3 * |
| 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)》.2012,160-161. * |
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