CN104290921A - Pneumatic damping speed reducer structure capable of being unfolded through air inflation - Google Patents

Abstract

The invention discloses a pneumatic damping speed reducer structure capable of being unfolded through air inflation. The pneumatic damping speed reducer structure capable of being unfolded through air inflation is a rigid-flexible combined body mainly composed of an arc rigid blunt head and an air inflation unfolding structure made of fabric fiber composites. The unfolding process of the pneumatic damping speed reducer structure capable of being unfolded through air inflation comprises the steps of unfolding of first-stage piled inflation unfolding rings of different diameters and unfolding of second-stage unfolding rings. The pneumatic damping speed reducer structure capable of being unfolded through air inflation further comprises coarse adjustment control blocks and fine adjustment control blocks, the coarse adjustment control blocks enable two mass blocks to move in union along a rail to achieve coarse adjustment, and a smaller mass block is moved along the rail so that fine adjustment of a mass center control disc can be achieved. The control over postures of a speed reducer in four directions can be achieved by moving and synergistically adjusting the mass center control blocks in the four directions. The pneumatic damping speed reducer structure capable of being unfolded through air inflation is low in structural mass and forms a large resistance plane through rapid inflation shape setting. Due to the fact that the pneumatic damping speed reducer structure is mainly made of the fabric fiber composites, the pneumatic damping speed reducer structure capable of being unfolded through air inflation can be efficiently and conveniently folded and is small in launching size.

Description

A kind of inflating expanded aerodynamic damping reducer structure

Technical field

The invention belongs to damp speed reducer technical field, specifically relate to a kind of inflating expanded aerodynamic damping reducer structure.

Background technology

Along with space industry and deep space explore the development of task, reenter and return means of delivery to be subject to the restriction of fairing of launch vehicle size more and more obvious.Laboratory, space station provides precious resources for carrying out space life science research, space station can have been utilized to carry out a large amount of biologies and medical experiment, due to the ageing requirement that biological experiment sample has it special, namely after experiment terminates, require sample Treatment Analysis as early as possible, to guarantee that data are accurate, there is scientific meaning.As space microgravity biomedicine learns experiment, general continuous days or several weeks left and right time, the sample of fixing or cracking as can not be at once analyzed, then needs Cord blood.At present, the equipment analyzed in-orbit has been difficult to, and the volume of refrigeration resource is also very limited, seriously constrains carrying out of space life science research.The optimal path of head it off is exactly that biological specimen can return in time, in batches.If inflatable aerodynamic damping structure can be utilized to realize repeatedly return technique, just can realize and meet biological specimen in-orbit timely, return in batches, will effectively promote the development of Chinese Space life science.

Hypersonic inflatable aerodynamic damping structure is as a kind of new construction technology, and it is folded in load efficiently by resistant to elevated temperatures lightweight, flexible composite to enclose out of my cabin, reenters inflation before air.This structure mainly forms inflatable deployment structure, solar heat protection resistance area, air inflator system, rigidity nose cone, barycenter control system, payload module case etc. by the variable diameters inflation annulus of drum type section units and forms.The inflating expanded aerodynamic damping reducer structure of a lot of type and structure has been applied in prior art, but these structures can not meet fast-developing new demand simultaneously, comprise: lightweight, volume is little, development rate is fast, barycenter is controlled, low-speed operations time multiple requirements such as resistance is large, this inflating expanded aerodynamic damping reducer structure that just simultaneously can meet these new requirements for research and development proposes new problem.

Summary of the invention

In order to solve the problems of the technologies described above, the invention provides a kind of inflating expanded aerodynamic damping reducer structure, can meet lightweight, volume is little, development rate is fast, barycenter is controlled, low-speed operations time multiple requirement such as resistance is large, be applicable to repeatedly returning of sample in-orbit.

Technical scheme of the present invention is as follows:

A kind of inflating expanded aerodynamic damping reducer structure, comprises rigidity nose cone 10, the stacking inflating expanded annulus 2 of one-level different-diameter, one-level launches gas filling bottle 7, secondary launches gas filling bottle 14, control cock 6, gas conduit 11, up and down barycenter controll block 3, horizontal centroid control panel 13, bandage 12, standard assign case 8, secondary to launch annulus 1 and stretched film resistance area 15; It is characterized in that: described rigidity nose cone 10, one-level are launched gas filling bottle 7, up and down barycenter controll block 3, horizontal centroid control panel 13, standard and assigned case 8 to be positioned at retarder midway location successively to upper, rigidity nose cone 10 is positioned at bottom, and its cross section is approximated to fan-shaped; Described one-level is launched gas filling bottle 7 and is positioned at nose cone inside, and be subject to the protection of nose cone, horizontal centroid control panel 13 is located at rigidity nose cone 3 and standard is assigned between case 8; The annulus being close to rigidity nose cone 10 of the stacking inflating expanded annulus 2 of described one-level different-diameter is bundled on rigidity nose cone 10 by bandage 12, and other annulus are then successively by bandage 12 and the binding of adjacent annulus; Described control cock 6 is arranged on one-level and launches gas filling bottle 7 and be connected by the stacking inflating expanded annulus 2 of gas conduit 11 and one-level different-diameter; After retarder completes secondary expansion, secondary launches annulus 1 and is positioned at topmost, and stretched film resistance area 15 connects the stacking inflating expanded annulus 2 of the one-level different-diameter inner side of annulus and the outside of secondary expansion annulus 1 topmost; Described secondary launches to be provided with secondary in annulus 1 and launches gas filling bottle 14.

Preferably, described one-level is launched gas filling bottle 7 and is connected with rigidity nose cone by five beams, and one of them beam fixes the lower end that one-level launches gas filling bottle 7, and other four beams fix the surrounding that one-level launches gas filling bottle 7.

Preferably, the stacking inflating expanded annulus 2 of described one-level different-diameter to be extruded along the inside face direction of rigidity nose cone 10 by the individual layer annulus of different-diameter and stackingly forms or form by double-layer circular ring is stacking along the inside face direction of rigidity nose cone 10.

Preferably, four coarse adjustment horizontal centroid controll blocks 4 and four fine setting horizontal centroid controll blocks 5 are provided with in described horizontal centroid control panel 13.

Preferably, adopt dichotomous binding method to carry out staggered binding by band 12 between the annulus that the stacking inflating expanded annulus 2 of described one-level different-diameter is adjacent, binding mode is radially every 22.5 degree of radial bands 12.

Preferably, the outside face of the stacking inflating expanded annulus 2 of described one-level different-diameter designs one deck thermal insulation film structure 9.

Preferably, the inner side annulus of described rigidity nose cone 10 and the stacking inflating expanded annulus 2 of one-level different-diameter is connected by bandage 12, and described rigidity nose cone 10 comprises eight groups or 12 groups of rivet holes 16, often organizes four rivets 16; Inner side annulus adopts eight or 12 bands to be connected on rigidity nose cone 10.

Preferably, described control cock 6 is four, is connected by the stacking inflating expanded annulus 2 of four gas conduits 11 and one-level different-diameter, and described inflating expanded aerodynamic damping reducer structure launches rear adjacent gas conduit 11 completely mutually in 90 degree of angles.

Preferably, the outmost turns of the stacking inflating expanded annulus 2 of described one-level different-diameter is provided with a fine circle 17.

Preferably, be separate space between the inflation ring of the different-diameter of the stacking inflating expanded annulus 2 of described one-level different-diameter, adopt the inflation strategy that the two-side synchronous of ecto-entad launches.

Preferably, the stacking inflating expanded annulus 2 of described one-level different-diameter is made up of many subelements, and each subelement is made up of two circular arcs and pair of parallel line, and described parallel lines is perpendicular to the bus of retarder resistance area; Two described circular arcs are the part on same circle, and radius of curvature is d/2, and 150mm≤d≤300mm, the spacing of two parallel liness is (d/2) ².

Preferably, the minimum value of the inflation pressure in the stacking inflating expanded annulus 2 of described one-level different-diameter is:

$p_{\min }=F\frac{4\tan \mathrm{\α}\sin \mathrm{\α}}{3\mathrm{\πDd}}$

Wherein F is aerodynamic drag, and D is the vertical projection bore of inflatable aerodynamic damping structure, and d is the diameter of single inflation annulus, and α is the angle between aerodynamic damping structural drag face and axis.

Innovative point of the present invention is as follows:

(1) dual-stage inflators expansion technique is adopted: the inflating expanded and secondary of the stacking inflating expanded annulus of one-level different-diameter launches annulus tensioning fabric fiber composite materials resistance area;

(2) for the gesture stability problem of inflating expanded aerodynamic damping reducer structure ablated configuration, the sectional type proposed becomes more meticulous the controlled method of adjustment of barycenter;

(3) the dichotomous binding mode of inflating expanded aerodynamic damping reducer structure is formed for the stacking annulus of different-diameter;

(4) constructional feature: the resistance area structure of inflating expanded rear formation super large caliber, structure adopts the rigidity inflatable deployment structure that is blunt nosed and that be made up of fabric fibre composite material of arc to form hard and soft fabricate block, during folding gathering, there is again very little transmitting volume, centre-line load on the one hand the barycenter of control structure can control flight attitude, there is standard install bin to return the design of object on the other hand, be beneficial to the recovery of load.

The rigidity inflatable deployment structure that is blunt nosed and that be made up of fabric fibre composite material of inflating expanded aerodynamic damping reducer structure of the present invention mainly arc forms hard and soft fabricate block, and architecture quality is light; Fast aeration is shaping, forms large-area resistance area.Owing to mainly adopting fabric fibre composite material to make, be convenient to the folding expeditiously of inflating expanded aerodynamic damping reducer structure and draw in, launch volume little.

Inflating expanded aerodynamic damping reducer structure of the present invention relate to 9 barycenter controll blocks, for solving the gesture stability problem in retarder flight course, be respectively upper and lower barycenter adjustment block 3, horizontal centroid control panel 13, wherein horizontal centroid control panel 13 is positioned at standard install bin 8 lower end, be close to nose cone 8, upper and lower barycenter adjustment block 3 slideway bar connects one-level and launches gas filling bottle 7 and horizontal centroid control panel 13 (see Fig. 4), can play the effect that fixing one-level launches gas cylinder; When retarder needs barycenter to control flight attitude, centroid detection system can pass to barycenter control system by electric signal, if when barycenter needs to regulate by a relatively large margin, then moved the coarse adjustment controll block 4 of relevant position by electric signal, namely two masses realize coarse adjustment along slideway together movement; When attitude needs fine setting, barycenter control panel is regulated by vernier control block 5, namely only moves less mass 5 along slideway; By mobile four orientation barycenter controll block synergic adjustment, the control to retarder four direction attitude can be realized.

Inflating expanded aerodynamic damping reducer structure of the present invention adopts the stacking inflating expanded annulus 2 of one-level different-diameter, single stacked rings cross section as shown in Figure 2, greatly can increase the area of contact between annulus, increase the friction force between adjacent rings, and between each stacking annulus, adopt dichotomous binding method (Fig. 6) to bundle, substantially increase the strength and stiffness of retarder inflation ring; The inflating expanded aerodynamic damping reducer structure expansion process that the present invention relates to comprises the expansion of the stacking inflating expanded annulus 2 of one-level different-diameter and the expansion of secondary expansion annulus 1, stacking inflating expanded annulus 2 rigidity of one-level different-diameter is larger, be applicable to the retarder that hypersonic speed runs, when retarder flying speed is lower, secondary launches annulus 1 and launches to drive stretched film face 15 to launch, make the effective resistance area of retarder add 4 times, increase resistance during flight.

In addition, the invention allows for pressure design formula in inflation ring.The inflating expanded damp speed reducer of the present invention's design is made primarily of the film that rigidity is lower, and its rigidity provides primarily of the inflation pressure in inflation ring.In order to ensure that retarder does not cause unstability in flight course, need to ensure to have certain inflation pressure in inflation ring, therefore the minimum pressure of the present invention to inflation ring designs, and namely when aerodynamic drag is F, the gaseous tension minimal design in inflation ring is:

$p_{\min }=F\frac{4\tan \mathrm{\α}\sin \mathrm{\α}}{3\mathrm{\πDd}}$

F is aerodynamic drag, and D is the vertical projection bore of inflatable aerodynamic damping structure, and d is the diameter of single inflation annulus, and α is the angle between aerodynamic damping structural drag face and axis.

Structure of the present invention ensure that can to inflate for several times in decline process to be increased drag area, reduce ballistic coefficient, reduces hot fluid temperature, finally decelerates to the landing speed of license.Structure of the present invention have lightweight, volume is little, development rate is fast, barycenter is controlled, low-speed operations time resistance large feature, a kind of actv. means can be provided for the landing of aircraft.

Accompanying drawing explanation

Fig. 1 is the schematic diagram (upper figure) of inflating expanded aerodynamic damping reducer structure, the schematic diagram (figure below) of barycenter control methods;

Fig. 2 is the schematic diagram of the single ring cross-section shape and size of the stacking inflating expanded annulus of one-level different-diameter;

Fig. 3 is the schematic diagram of the horizontal centroid control panel (13 in Fig. 1) of reducer structure, and upper figure is birds-eye view, and figure below is front view;

Fig. 4 is rigidity nose cone and inner structure schematic diagram thereof;

Fig. 5 is the schematic diagram (birds-eye view) of bandage connection mode between rigidity nose cone from different stacking circular ring structure;

Fig. 6 is the schematic diagram (birds-eye view) of bandage fixed form between the stacking annulus of inflating expanded aerodynamic damping reducer structure different-diameter;

Fig. 7 is the air inflator system design drawing of the different-diameter inflation ring of the stacking inflating expanded annulus of one-level different-diameter;

Fig. 8 is the schematic diagram of the resistance area structure of double-deck stacking annulus.

Detailed description of the invention

Below in conjunction with accompanying drawing and embodiment, the present invention is described in further details.

In a detailed description of the invention, as shown in Figure 1, the inflating expanded aerodynamic damping reducer structure of one of the present invention, comprises rigidity nose cone 10, the stacking inflating expanded annulus 2 of one-level different-diameter, one-level launches gas filling bottle 7, secondary launches gas filling bottle 14, control cock 6, gas conduit 11, up and down barycenter controll block 3, horizontal centroid control panel 13, bandage 12, standard assign case 8, secondary to launch annulus 1 and stretched film resistance area 15; Described rigidity nose cone 10, one-level are launched gas filling bottle 7, up and down barycenter controll block 3, horizontal centroid control panel 13, standard and are assigned case 8 to be positioned at retarder midway location successively to upper, and rigidity nose cone 10 is positioned at bottom, and its cross section is approximated to fan-shaped; Described one-level is launched gas filling bottle 7 and is positioned at nose cone inside, and be subject to the protection of nose cone, horizontal centroid control panel 13 is located at rigidity nose cone 3 and standard is assigned between case 8; The annulus being close to rigidity nose cone 10 of the stacking inflating expanded annulus 2 of described one-level different-diameter is bundled on rigidity nose cone 10 by bandage 12, and other annulus are then successively by bandage 12 and the binding of adjacent annulus; Described control cock 6 is arranged on one-level and launches gas filling bottle 7 and be connected by the stacking inflating expanded annulus 2 of gas conduit 11 and one-level different-diameter; After retarder completes secondary expansion, secondary launches annulus 1 and is positioned at topmost, and stretched film resistance area 15 connects the stacking inflating expanded annulus 2 of the one-level different-diameter inner side of annulus and the outside of secondary expansion annulus 1 topmost; Described secondary launches to be provided with secondary in annulus 1 and launches gas filling bottle 14.

Rigidity nose cone 10 plays the effect that protection one-level launches gas filling bottle 7 and corresponding four control cock 4 and upper and lower barycenter controll block 3; Horizontal control panel 13 is for regulating retarder horizontal centroid; After retarder completes secondary expansion, secondary launches annulus 1 and is positioned at topmost, the outside of inner side and secondary expansion annulus 1 that stretched film resistance area 15 connects one-level different-diameter stacking inflating expanded annulus 2 the top annulus is as Fig. 1, greatly can improve resistance during retarder low-speed operations, in addition, the secondary that secondary launches to install in annulus launches gas filling bottle 14, can realize the rapid deployment of secondary inflation ring.

Structure of the present invention need in moderating process twice inflating expanded, during retarder high-speed flight, only launch the thermal insulation film structure 9 of the stacking inflating expanded annulus 2 of one-level different-diameter and its outside face; When retarder speed flying speed is lower, need to carry out secondary inflating expanded time, open the valve that secondary launches gas cylinder 14, realize the expansion that stretched film resistance area 15 and secondary inflate annulus 1.Therefore, the resistance area that the present invention can realize under friction speed condition slows down, and wherein retarder secondary launches 4 times of rear effective resistance area one-level expansion effective resistance area.

Structure of the present invention comprises two and launches gas filling bottle, and one-level launches gas filling bottle 7 and secondary launches gas filling bottle 14, and wherein one-level expansion gas filling bottle is positioned at rigidity solar heat protection nose cone, for spherical or cylindrical, only inflates the stacking inflation annulus of various outer diameter; Secondary air inflator system is positioned at secondary and launches annulus, (can prevent from producing damage to inflation ring for spherical, only launch annulus to secondary and inflate, namely just use during retarder second outspread; With only comprise compared with a gas filling bottle, the present invention uses less breather pipe, avoids the impact of too much appendix on second outspread stretched film face, realizes the rapid deployment of reducer structure.

Structure of the present invention comprises standard and assigns case 8 as a part for inflating expanded aerodynamic damping reducer structure, makes inflating expanded aerodynamic damping reducer structure can realize low cost recovery standard and assigns efficiency test load in case; Standard assigns case can realize reclaiming capacity weight standard interface module and suitability, reduces capacity weight owing to being subject to the infringement vibrated and thermal load produces.Inflating expanded aerodynamic damping reducer structure realizes being arranged on (such as manned space station) on certain aircraft, when needs make efficiency test load download to return to ground, case is assigned to install inflating expanded aerodynamic damping reducer structure the standard containing efficiency test load, priming system carries out unblock and is separated with (such as manned space station) on certain aircraft, and the efficiency test load that the standard in inflating expanded aerodynamic damping reducer structure is assigned case to carry and need be reclaimed returns to ground safely.

In another embodiment, as shown in Figure 4, described one-level is launched gas filling bottle 7 and is connected with rigidity nose cone by five beams, and one of them beam fixes the lower end that one-level launches gas filling bottle 7, and other four beams fix the surrounding that one-level launches gas filling bottle 7.

In another embodiment, as illustrated in figures 1 and 8, the stacking inflating expanded annulus 2 of described one-level different-diameter to be extruded along the inside face direction of rigidity nose cone 10 by the individual layer annulus of different-diameter and stackingly forms or form by double-layer circular ring is stacking along the inside face direction of rigidity nose cone 10.

In another embodiment, as shown in figures 1 and 3, four coarse adjustment horizontal centroid controll blocks 4 and four fine setting horizontal centroid controll blocks 5 are provided with in described horizontal centroid control panel 13, the barycenter that can realize retarder controls, comprise the adjustment up and down 3 of barycenter, horizontal centroid adjustment disk 13, horizontal adjustment control panel there are four groups of barycenter adjustment blocks, often organize barycenter adjustment block and comprise two masses, movement can realize coarse adjustment 4 together, only Internal moving mass motion realizes fine setting 5, in retarder flight course, can facilitate and adjust gearbox attitude accurately, this retarder aircraft centroid adjustment mode, can realize the quick adjusting of attitude

In another embodiment, as shown in Figure 6, adopt dichotomous binding method to carry out staggered binding by band 12 between the annulus that the stacking inflating expanded annulus 2 of described one-level different-diameter is adjacent, binding mode is radially every 22.5 degree of radial bands 12; Retarder bulk strength and rigidity can be improved.

In another embodiment, as illustrated in figures 1 and 8, the outside face of the stacking inflating expanded annulus 2 of described one-level different-diameter designs one deck thermal insulation film structure 9, can meet smooth pneumatic appearance, can realize thermal protective performance again.

In another embodiment, as shown in Figure 5, the inner side annulus of described rigidity nose cone 10 and the stacking inflating expanded annulus 2 of one-level different-diameter is connected by bandage 12, and described rigidity nose cone 10 comprises eight groups or 12 groups of rivet holes 16, often organizes four rivets 16; Inner side annulus adopts eight or 12 bands to be connected on rigidity nose cone 10.

In another embodiment, as shown in Figure 4, described control cock 6 is four, is connected by the stacking inflating expanded annulus 2 of four gas conduits 11 and one-level different-diameter, and described inflating expanded aerodynamic damping reducer structure launches rear adjacent gas conduit 11 completely mutually in 90 degree of angles.

In another embodiment, as illustrated in figures 1 and 8, the outmost turns of the stacking inflating expanded annulus 2 of described one-level different-diameter is provided with a fine circle 17, suppressing the gas detour flow produced during damping structure flight during the effect that it designs, improving because streaming the fugitiveness causing structure to fly.

In another embodiment, be separate space between the inflation ring of the different-diameter of the stacking inflating expanded annulus 2 of described one-level different-diameter, adopt the inflation strategy (Fig. 7) that the two-side synchronous of ecto-entad launches.This inflation strategy solves initial gathering in and is folded in the structurally ordered reliable fast speed expansion problems of inflation resistance area, be its effect of separate space between the inflation ring of different-diameter be, after avoiding a certain ring to leak gas on the one hand, involve total inflation; Can inflate expeditiously on the other hand, a ring inflation independently can play penumatic stiffness, forms resistance area and realizes damping deceleration.Except being UNICOM between the CV0 that CV1 and suppression are streamed.First high-pressure gas bottle is inflated to CV1 and inner loop CV0, when reaching design pressure, closes electrically-controlled valve 1; Start to inflate in CV2, when reaching design pressure, close electrically-controlled valve 2.In like manner, start to inflate in CVn, when reaching design pressure, close electrically-controlled valve n.It is the order of same ring bilateral symmetry inflation synchronous expansion, the stable and expansion of holding structure in this gas replenishment process.

In another embodiment, the stacking inflating expanded annulus 2 of described one-level different-diameter is made up of many subelements, and each subelement is made up of two circular arcs and pair of parallel line, and described parallel lines is perpendicular to the bus of retarder resistance area; Two described circular arcs are the part on same circle, and radius of curvature is d/2, and 150mm≤d≤300mm, the spacing of two parallel liness is (d/2) ².Only have when parallel lines distance is (d/2) ²time, the maximum stress that film tube bears at the same pressure is minimum.As shown in Figure 2, wherein ∠ AOB is the size of the rigidity nose cone cone angle of retarder, and parallel lines is not level, and it is vertical with the bus of retarder resistance area.

In another embodiment, the minimum value of the inflation pressure in the stacking inflating expanded annulus 2 of described one-level different-diameter is:

$p_{\min }=F\frac{4\tan \mathrm{\α}\sin \mathrm{\α}}{3\mathrm{\πDd}}$

Wherein F is aerodynamic drag, and D is the vertical projection bore of inflatable aerodynamic damping structure, and d is the diameter of single inflation annulus, and α is the angle between aerodynamic damping structural drag face and axis.

A kind of inflating expanded aerodynamic damping reducer structure provided by the invention is that the reducer structure that the gas produced by nose cone place gas filling bottle makes to fold launches, its working process is as follows: when needs reducer structure works, an electric signal is produced to gas filling bottle by the external world, open the gas-filled switching tube at head standard place, gas is filled with the stacking inflating expanded annulus of one-level, open one-level inflation annulus, now radial binding ribbon is tied tight, can ensure the Rigidity and strength of retarder.Subsequently, until retarder speed be reduced to need to open secondary inflation ring time, the extraneous gas filling bottle opened by electric signal in secondary inflation annulus, realize the inflating expanded deceleration in the second stage (after launching, retardation area is 2 times that one-level is launched), thus reduce the flying speed of retarder further.

Claims (10)

1. an inflating expanded aerodynamic damping reducer structure, comprises rigidity nose cone (10), the stacking inflating expanded annulus (2) of one-level different-diameter, one-level launches gas filling bottle (7), secondary launches gas filling bottle (14), control cock (6), gas conduit (11), up and down barycenter controll block (3), horizontal centroid control panel (13), bandage (12), standard assign case (8), secondary to launch annulus (1) and stretched film resistance area (15); It is characterized in that: described rigidity nose cone (10), one-level are launched gas filling bottle (7), up and down barycenter controll block (3), horizontal centroid control panel (13), standard and assigned case (8) to be positioned at retarder midway location successively to upper, rigidity nose cone (10) is positioned at bottom, and its cross section is approximated to fan-shaped; Described one-level is launched gas filling bottle (7) and is positioned at nose cone inside, and be subject to the protection of nose cone, horizontal centroid control panel (13) is located at rigidity nose cone (3) and standard is assigned between case (8); The annulus being close to rigidity nose cone (10) of the stacking inflating expanded annulus (2) of described one-level different-diameter is bundled on rigidity nose cone (10) by bandage (12), and other annulus are then successively by bandage (12) and the binding of adjacent annulus; Described control cock (6) is arranged on one-level and launches gas filling bottle (7) and be connected with the stacking inflating expanded annulus (2) of one-level different-diameter by gas conduit (11); After retarder completes secondary expansion, secondary launches annulus (1) and is positioned at topmost, and stretched film resistance area (15) connects the stacking inflating expanded annulus (2) of the one-level different-diameter inner side of annulus and the outside of secondary expansion annulus (1) topmost; Described secondary launches to be provided with secondary in annulus (1) and launches gas filling bottle (14).

2. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, is characterized in that: the stacking inflating expanded annulus of described one-level different-diameter (2) to be extruded along the inside face direction of rigidity nose cone (10) by the individual layer annulus of different-diameter and stackingly forms or form by double-layer circular ring is stacking along the inside face direction of rigidity nose cone (10).

3. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, is characterized in that: be provided with four coarse adjustment horizontal centroid controll blocks (4) and four fine settings horizontal centroid controll block (5) in described horizontal centroid control panel (13).

4. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, it is characterized in that: adopt dichotomous binding method to carry out staggered binding by band (12) between the annulus that the stacking inflating expanded annulus of described one-level different-diameter (2) is adjacent, binding mode is radially every 22.5 degree one radial band (12).

5. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, it is characterized in that: the inner side annulus of described rigidity nose cone (10) and the stacking inflating expanded annulus (2) of one-level different-diameter is connected by bandage (12), described rigidity nose cone (10) comprises eight groups or 12 groups of group rivet holes (16), often organizes four rivets (16); Inner side annulus adopts eight or 12 bands to be connected on rigidity nose cone (10).

6. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, it is characterized in that: described control cock (6) is four, be connected by the stacking inflating expanded annulus (2) of four gas conduits (11) and one-level different-diameter, described inflating expanded aerodynamic damping reducer structure launches rear adjacent gas conduit (11) completely mutually in 90 degree of angles.

7. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, is characterized in that: the outmost turns of the stacking inflating expanded annulus (2) of described one-level different-diameter is provided with a fine circle (17).

8. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, it is characterized in that: be separate space between the inflation ring of the different-diameter of the stacking inflating expanded annulus (2) of described one-level different-diameter, adopt the inflation strategy that the two-side synchronous of ecto-entad launches.

9. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, it is characterized in that: the stacking inflating expanded annulus (2) of described one-level different-diameter is made up of many subelements, each subelement is made up of two circular arcs and pair of parallel line, and described parallel lines is perpendicular to the bus of retarder resistance area; Two described circular arcs are the part on same circle, and radius of curvature is d/2, and 150mm≤d≤300mm, the spacing of two parallel liness is (d/2) ².

10. the inflating expanded aerodynamic damping reducer structure of one according to claim 1, is characterized in that: the minimum value of the inflation pressure in the stacking inflating expanded annulus (2) of described one-level different-diameter is:

$p_{\min }=F\frac{4\tan \mathrm{\α}\sin \mathrm{\α}}{3\mathrm{\πDd}}$

Wherein F is aerodynamic drag, and D is the vertical projection bore of inflatable aerodynamic damping structure, and d is the diameter of single inflation annulus, and α is the angle between aerodynamic damping structural drag face and axis.