CN109737826A - One seed level structure - Google Patents
One seed level structure Download PDFInfo
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- CN109737826A CN109737826A CN201910140761.XA CN201910140761A CN109737826A CN 109737826 A CN109737826 A CN 109737826A CN 201910140761 A CN201910140761 A CN 201910140761A CN 109737826 A CN109737826 A CN 109737826A
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- air bag
- rocket body
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- level structure
- head
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Abstract
The present invention discloses a seed level structure, including rocket body, aerodynamic decelerator mechanism and pneumatic anticollision mechanism.Aerodynamic decelerator mechanism includes pneumatic head and burn-out proof layer, and pneumatic head is the second air bag that can be collapsed and be unfolded, and the second air bag is located at outside the head of rocket body；Pneumatic anticollision mechanism has the first air bag that can be collapsed and be unfolded, and the first air bag is located at outside the tail portion of rocket body.Second air bag is filled with air in symmetrical structure, has good aerodynamic stability.It sets up defences on the outer wall of the second air bag ablation layer, be burned out second air bag will not when flight in altitude high temperature, the second air bag can slow down to rocket body in altitude high temperature；And buffer function is played to rocket body when low latitude is landed, the second air bag has foldability, reduces the second air bag the space occupied and weight on rocket body；Meanwhile first air bag can rocket body tail portion land when, to tail portion flexible buffer act on, prevent rocket body to be damaged.
Description
Technical field
The present invention relates to the space technology fields of Solid Launch Vehicle, and in particular to a seed level structure.
Background technique
In different trajectory return courses, sub- level structure separates the sub- level structure of Solid Launch Vehicle with pole structure above
Afterwards, sub- level structure also will continue to leap high to extra-atmospheric flight for a period of time due to effect of inertia, again return to the earth later
Endoatmosphere, and then land on the ground.Current sub- level structure mainly includes rocket body and the front segment structure for being located at rocket body head
And the rear section structure positioned at rocket body back segment.It mainly include deceleration device, navigational guidance and control system, posture control in front segment structure
The equipment such as system processed.Group level structure returns in the downward landing mission of earth atmosphere, and deceleration device is by increasing and extraneous gas
The frictional resistance of body reduces the flying speed of sub- level structure, so that sub- level structure safe landing is on the ground.
Since sub- level structure is entering the high in the air with high-speed flight, rocket body and a large amount of heat of atmosphere friction generation of atmosphere
Amount, the heat make environment locating for rocket body be hot environment, and high temperature is easy to burn deceleration device, and deceleration device is needed to have one
Determine Burning corrosion resistance, but existing parachute is unable to high temperature resistant, is easy to be burned out in the high temperature environment；The decline of group level structure
When to low latitude, when especially sub- level structure will land on the ground, and need deceleration device that there is certain flexible buffer effect, with
It prevents deceleration device from hitting with the direct hard hit in ground, damages rocket body.In addition, convenient for recycling rocket body, it is also necessary to which deceleration device is slowing down
Aerodynamic stability in the process is preferable, and the Randomness of position after otherwise rocket body lands is too big, is not easy to give rocket body for change.
For meet it is above-mentioned to deceleration device the needs of, deceleration device in the prior art is usually arranged one in high temperature high-altitude
The retarder that slow down to rocket body and the parachute for carrying out deceleration landing to rocket body in low latitude.Wherein, retarder has rigidity
Solar heat protection is blunt nosed greatly, since the big blunt nosed diameter is along its axial direction, gradually increases from head towards tail portion and is in symmetrical structure, with
Increase the stability of the big blunt nosed resistance and flight；Meanwhile it is big it is blunt nosed be made of rigidity and heat-resisting material so that this is just
Property retarder can altitude high temperature environment to rocket body carry out reduction of speed, when rocket body drops to low latitude, deployment covers
On big blunt nosed and rocket body the head of solar heat protection, parachute plays buffer function to the landing of rocket body, realizes that the installation of rocket body is landed.
The deceleration device of above structure, in order to enable deceleration device, in down speeding procedure, deceleration device has required gas
Dynamic stability, Burning corrosion resistance and the cushion performance of landing, needing to be separately provided one has the big blunt nosed retarder of rigid solar heat protection
And parachute, still, the retarder of two kinds of forms combines, so that structure is complicated for entire deceleration device；Especially rigid solar heat protection is slowed down
Head is unable to folding storage, and the space occupied is big, and the weight for carrying sub- level structure is big, at high cost required for rocket body recycling.
Meanwhile sub- level structure, when landing, the head of the rocket body of sub- level structure is first landed, the tail portion of the rocket body of sub- level structure
It lands, but is not provided with any safeguard structure on the tail portion of existing sub- level structure, directly hit on the ground, punching is generated to rocket body
Power is hit, to damage rocket body.
Summary of the invention
Therefore, technical problem to be solved by the present invention lies in existing sub- level structure, structure is complicated, weight is big and arrow
Body landing tail portion is easy to hit bad.
For this purpose, the present invention provides a seed level structure, including
Rocket body；
Pneumatic anticollision mechanism is located on the rocket body and has what can be converted between rounding state and unfolded state to fill
First air bag of gas；
Aerodynamic decelerator mechanism is located on the rocket body comprising
Pneumatic head, for inflatable second air bag that can be converted between rounding state and unfolded state；Second gas
Capsule in the unfolded state in the diameter of rotational-like and described second air bag along its axial direction by the windward side court of the second air bag
It is gradually increased to the leeward direction of the second air bag；
At least one layer of burn-out proof layer, is located in the outside wall surface of the second air bag；
First air bag and the second air bag are in unfolded state suitable for being located at the tail portion and head of the rocket body respectively
Outside.
Optionally, above-mentioned sub- level structure, the aerodynamic decelerator mechanism further include be located at second gasbag ektexine face with
At least one layer of thermal insulation layer between the burn-out proof layer.
Optionally, above-mentioned sub- level structure, second air bag include falling on head and the end for being located at the head
Cone, the bus on the head are smooth curve.
Optionally, above-mentioned sub- level structure, the head are in spherical crown shape.
Optionally, above-mentioned sub- level structure, second air bag and the/the first air bag include being sequentially connected end to end along its circumferential direction
At least two air bags；
The two neighboring branch air sac sealing separates, and each branch air bag is equipped with inflating port.
Optionally, above-mentioned sub- level structure, two branch air bags of arbitrary neighborhood are by being located in first air bag at respective place
Or the second flexible character of flexible ribs in air bag seals partition；Or
At least one flexible character of flexible ribs is provided in any air bag；Alternatively, be provided in the first air bag or the second air bag to
A few flexible character of flexible ribs, the flexible character of flexible ribs circumferentially cross over all air bags along respectively place air bag.
Optionally, above-mentioned sub- level structure, when being provided at least one flexible character of flexible ribs in any air bag；Alternatively, first
At least one flexible character of flexible ribs is provided in air bag or the second air bag, the flexible character of flexible ribs crosses over institute along the circumferential direction of respectively place air bag
When having branch air bag, the flexible character of flexible ribs is at least two, and all flexible character of flexible ribs are in stacking along the axial direction of respectively place air bag
It arranges on corresponding air bag.
Optionally, above-mentioned sub- level structure, first air bag and/or the second air bag are by being inlaid in respective leeward
The rigid connector in sunk area surrounded is to be fixed on the rocket body；
Second air bag or the first air bag are suitable for covering corresponding rigid connector.
Optionally, above-mentioned sub- level structure, the rigid connector is by telescopic component along the axial direction of respectively place air bag
Telescopically it is located on rocket body.
Optionally, above-mentioned sub- level structure, first air bag is in the unfolded state in rotational-like and described the
The diameter of one air bag is gradually increased along its axial direction by the leeward direction of windward side towards the first air bag of the first air bag.
Technical solution of the present invention has the advantages that
1. sub- level structure provided by the invention, including aerodynamic decelerator mechanism and pneumatic anticollision mechanism, wherein aerodynamic decelerator machine
Structure includes pneumatic head and at least one layer of burn-out proof layer, and pneumatic head is inflatable for that can convert between rounding state and unfolded state
The second air bag；Second air bag in the unfolded state in the rotational-like head suitable for being located at rocket body outside；Second
Diameter of the air bag in unfolded state along its axial direction by the second air bag windward side towards the second air bag leeward direction gradually
Increase, so that the second air bag is filled with air axisymmetricly, there is good aerodynamic stability in flight course；In the second air bag
Outside wall surface on setting burn-out proof layer, since burn-out proof layer is other than its heat-proof quality, due also to it vaporization when can inhale
A large amount of heat is received, to reduce the temperature of air bag local environment, even if burn-out proof layer burns, can also take away certain heat,
The temperature for reducing air bag local environment, be burned out second air bag will not when flight in altitude high temperature, thus the second air bag
It can slow down in altitude high temperature to rocket body；And buffer function is played to rocket body when low latitude is landed, the second air bag is in unaerated
It may be at rounding state before, reduce the second air bag the space occupied and weight on rocket body.That is, only need to be in the head of rocket body
Portion is equipped with the aerodynamic decelerator mechanism of the application, which has just entered atmosphere from rocket body and begun to subtract rocket body
Speed, until rocket body landing ground location, to simplify the structure of existing deceleration device；Meanwhile pneumatic anticollision mechanism can collapse
The first air bag converted between state and unfolded state outside the tail portion that the first air bag is located at rocket body in unfolded state, works as arrow
When the tail portion of body is landed, due to the buffer function of the first air bag, to play a protective role to rocket body, rocket body is avoided to damage.
2. sub- level structure provided by the invention, aerodynamic decelerator mechanism further include be located at second gasbag ektexine face with it is described
At least one layer of thermal insulation layer between burn-out proof layer is arranged multilayer insulation, further improves the second air bag in altitude high temperature ring
Heat-resisting quantity in border, even if after burn-out proof is burned out, still being able to so that the second air bag slows down under high temperature environment.
3. sub- level structure provided by the invention, the second air bag includes the back taper on head and the end for being located at the head
Body；The bus on the head is smooth curve；Carrying out ground improves the shape and aerodynamic stability of pneumatic head.
4. Zi Ji mechanism provided by the invention, the first air bag and/or the second air bag include being sequentially connected end to end along its circumferential direction
At least two air bags；The two neighboring branch air sac sealing separates, and each branch air bag is equipped with inflating port, Duo Gezhi
Air bag is mutually indepedent, even if the sealing of part branch air bag is poor, will not influence the air-tightness of other branch air bags, further improve
The air-tightness of first air bag or the second air bag, prolongs its service life.
It further include flexible character of flexible ribs 5. sub- level structure provided by the invention, flexible character of flexible ribs is to the second air bag or the first air bag
Shape is limited, and the impact forces in the anti-external world of air bag are enhanced, so that pneumatic head has stable structure and higher-strength, simultaneously
Good aerodynamic configuration is kept, the aerodynamic stability or anticollision of air bag are further improved.
6. sub- level structure provided by the invention, the pneumatic head passes through the rigid connector that is inlaid in the sunk area
To be fixed on the rocket body；The sunk area of second air bag is suitable for covering the head of the rigid connector and rocket body
On, in high temperature high altitude environment, the second air bag plays the role of thermal protection to the head of rigid connector and rocket body, so that rigidity connects
The not direct and extraneous high temperature contact in the head of fitting and rocket body.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art be briefly described, it should be apparent that, it is described below
Attached drawing is some embodiments of the present invention, for those of ordinary skill in the art, before not making the creative labor
It puts, is also possible to obtain other drawings based on these drawings.
Fig. 1 is the schematic diagram of the sub- level structure provided in the embodiment of the present invention 1；
Fig. 2 is the partial schematic diagram of the sub- level structure provided in the embodiment of the present invention 1；
Fig. 3 is the structural schematic diagram of the positive apparent direction of the aerodynamic decelerator mechanism provided in the embodiment of the present invention 1；
Fig. 4 is the schematic diagram of the pneumatic head of the aerodynamic decelerator mechanism in Fig. 3；
Fig. 5 is the structural schematic diagram of the side-looking direction of the pneumatic head of Tu3Zhong aerodynamic decelerator mechanism；
Fig. 6 is the partial cutaway schematic of the pneumatic head of Tu3Zhong aerodynamic decelerator mechanism；
Fig. 7 be Fig. 2 neutron level structure aerodynamic decelerator mechanism in telescopic rod, rigid connector and rocket body side-looking direction
Schematic diagram；
Fig. 8 is the structural schematic diagram of telescopic rod in Fig. 6；
Description of symbols:
The pneumatic head of 1-；The head 11-；12- reverse taper；13- branch air bag；14- flexible character of flexible ribs；
2- rigid connector；
31- thermal insulation layer；32- burn-out proof layer；
The first bar of 41-；The second bar of 42-；43- resilient latching member；
5- pack；
6- rocket body；
The first air bag of 7-.
Specific embodiment
Technical solution of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Example is a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill
Personnel's every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for description the present invention and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.In addition, term " first ", " second ",
" third " is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
As long as in addition, the non-structure each other of technical characteristic involved in invention described below different embodiments
It can be combined with each other at conflict.
Embodiment 1
The present embodiment provides a seed level structures, as shown in Figures 1 to 8, including rocket body, the gas being located on the head of rocket body
Dynamic deceleration mechanism, the pneumatic anticollision mechanism being located on rocket body tail portion.Wherein, aerodynamic decelerator mechanism includes pneumatic head 1, multilayer insulation
Layer 31, burn-out proof layer 32, rigid connector 2.
Specifically, pneumatic head 1 is inflatable second air bag that can be converted between rounding state and unfolded state；The
Two air bags in unfolded state in rotational-like and the second air bag diameter along its axial direction by the windward side of the second air bag towards the
The leeward direction of two air bags is gradually increased；The leeward of second air bag surrounds sunk area, when the second air bag is in unfolded state
When, which is located at outside the head of rocket body.Specifically, as shown in Figure 3 and Figure 4, the second air bag include head 11 and
The reverse taper 12 being located on the end on head 11, head 11 are in spherical crown shape, and the diameter of the second air bag is along its axial direction by head direction
Reverse taper direction gradually increases, so that second air bag, in the big blunt nosed of symmetrical structure, resistance coefficient is greatly and stable
Property is good.
As shown in figure 4, pneumatic head 1 is in the perspective view of vertical plane (plane where Y-axis and Z axis), back taper after inflation
Body 12 is trapezoidal in standing upside down, the tangent transition in end on side and head 11 where two waists for standing upside down trapezoidal, so that pneumatic head 1
Shape is streamlined in smoothly transitting, so that second air bag preferably meets the need of aerodynamic decelerator shape and aerodynamic stability
It asks.
The leeward of second air bag surrounds sunk area, and the second air bag passes through the rigid connector that is inlaid in sunk area
2 are fixed on rocket body, and rigid connector 2 is cylindrical, and are made of rigid material resistant to high temperature, for example, it is resistant to high temperature not
Become rusty steel pipe.As shown in Fig. 2, one end of rigid connector 2 is fixed on the head of rocket body 6, the other end, which successively seals, is threaded through
On the leeward and windward side on the head 11 of two air bags, the axis of rigid connector 2 is overlapped with the axis of pneumatic head 1, thus gas
Dynamic head 1 is symmetric on rigid connector 2, and rigid connector 2 plays the role of supporting and fixing to the second air bag, so that the
Two air bags are under ambient atmos effect, and the leeward of the second air bag is limited by rigid connector 2, so that the second air bag is further
Symmetrical contour structures are able to maintain, the aerodynamic stability of the second air bag is further improved.
As shown in Fig. 2, reverse taper 12 covers on outside the head of rigid connector 2 and rocket body, alternatively, reverse taper 12 is by rocket body
Head and middle part all cover, thermal insulation layer and burn-out proof layer (hereinafter refer to) of the second gasbag ektexine face equipped with multilayer, and second
Air bag covers rigid connector, so that the second air bag plays the role of thermal protection to rigid connector 2, avoids rigid connector 2 straight
It connects and is contacted with external high temperature environment.
To make pneumatic head 1 have better aerodynamic stability, position when convenient for its landing is in controlled range, also in arrow
Setting adjustment component (not illustrating in figure), is adjusted the posture of the second airbag deployment state, so that the second air bag on body 6
In symmetrical structure.
The adjustment component is equivalent to reaction control system(RCS) (RCS) or attitude control system.For example, adjustment component includes supplying
Mechanism of qi structure and multiple air jet pipes store high pressure gas in high pressure gas cylinder for example, gas supply mechanism is the high pressure gas cylinder being located on rocket body 6
Body.Multiple air jet pipes are fixed on rocket body bulkhead and are located in cabin inner cavity, connect with the outlet pipe of high pressure gas cylinder, spray
The nozzle of tracheae sprays high pressure gas against the aperture on bulkhead, and high pressure gas generates reaction after aperture sprays, to bulkhead
Power to drive rocket body to move, and then changes the air pocket motion being fixed on rocket body, with realize to the posture of air bag drawout into
Row adjustment.The outlet pipe of high pressure gas cylinder is equipped with valve, and flow control valve is arranged on the air inlet close to air jet pipe, just
In adjustment of the adjustment air jet pipe to bulkhead driving force, for example flow control valve is solenoid valve or shut-off valve.
In addition, the material of pneumatic head 1 can use nylon or other materials with certain flexibility, for example, carbon fiber
Dimension.Meanwhile jet pipe being located in 2 inner cavity of rigid connector, so that deceleration device is compact-sized.
As shown in Fig. 2, multilayer insulation 31 is set in the outside wall surface of pneumatic head 1, for example, three layers of thermal insulation layer 31 of setting, three
Layer thermal insulation layer 31 is respectively metal foil, carbon cloth and ceramic fibre or aramid fiber, aramid fiber, braiding ceramic fabric.Or three layers
Thermal insulation layer 31 is metal foil, and three layers of thermal insulation layer 31 are ceramic fibre or ceramic fabric etc..For example, ceramic fibre includes three oxygen
Change aluminium, silica, diboron trioxide etc. to work good according to required ratio, ratio can not limit, as long as ceramics can be prepared
Fiber.The material of thermal insulation layer can also be other existing materials resistant to high temperature.
Alternatively, thermal insulation layer 31 can also be two layers, one layer, four layers, five layers etc., specifically set the number of plies according to actual needs and
Speech.The number of plies of thermal insulation layer 31 is arranged more, stronger to the thermal protection effect of pneumatic head 1.Optionally, thermal insulation layer 31 and pneumatic head
It is fixed between 1 outside wall surface by glue sticking, is also fixed using glue sticking between the thermal insulation layer 31 of adjacent two layers.Or use it
He fixes at mode, for example forms the thermal insulation layer 31 of required thickness directly in the outside wall surface of pneumatic head 1 using spraying method, to preceding
After one layer of thermal insulation layer 31 solidifies, then apply the thermal insulation layer 31 of later layer.
As shown in figure 3, the outside wall surface of outermost thermal insulation layer 31 is equipped at least one layer of burn-out proof layer 32, for example, setting
The burn-out proof layer 32 of one or two layers or multilayer is set, burn-out proof layer 32 can be made of epoxy resin material.It is optional,
Burn-out proof layer 32 is coated on thermal insulation layer 31, when aerodynamic decelerator mechanism after a period of use, if part burn-out proof layer is burned out
Afterwards, it can burn coating ablation layer at position, so that the burn-out proof layer of the second air bag has recoverability, can repeat to make
With second air bag.As deformation, burn-out proof layer 32 can also be using other high molecular polymers or fiber.For example fiber is
Carbon fiber or carbon nano-tube fibre etc..
32 pairs of burn-out proof layer pneumatic heads 1 play the protective effect of burn-out proof, allow the second air bag in altitude high temperature ring
Slow down in border to rocket body；Meanwhile above-mentioned multilayer insulation 31 further reinforce the second air bag and external high temperature environment every
The function of heat, prevent the heat in external environment is from directly acting on the second air bag；Even if burn-out proof layer 32 is burned out,
The thermal insulation layer of multilayer still is able to play the second air bag heat-insulated effect, and the temperature of the second air bag is made to be far below its temperature burnt
Degree, so that the aerodynamic decelerator mechanism has required thermal protection function, it can be under the altitude high temperature for having just enter into atmosphere
Slow down to rocket body 6, until the second airbag safety lands.In addition, since the periphery of rigid connector 2 is by the second air bag
It surrounds, when pneumatic head 1 slows down under altitude high temperature environment, burn-out proof layer 32 and thermal insulation layer 31 on the second air bag, also to rigid
Property connector 2 plays the role of thermal protection.
For the second air bag, as shown in figure 4, the second air bag includes multiple gas being circumferentially sequentially connected end to end along it
Capsule 13, the two neighboring sealing of branch air bag 13 separate, and each branch air bag 13 is equipped with inflating port.
For example, the windward side of the second air bag and leeward are respectively adopted in the first flexible plate of monolith and the second flexible board
First flexible plate and the second flexible plate braiding or suture are fixed together by block later by way of similar " sewing ",
And it is circumferentially formed and seals against each other the multiple air bags 13 kept apart.That is, " the fixed seam " of two neighboring branch air bag 13, by two
A branch air bag 13 is fixed and sealing separates.
Inflating port is set on each air bag 13, each inflating port is connect by the first pipeline with air charging system, and first
Check valve is set on pipeline, to control whether air charging system is inflated into branch air bag 13.For example, air charging system is to be located at rocket body 6
On high-pressure aerated bottle.The respectively individually inflation of multiple air bags 13, even if a branch air bag 13 leaks, will not influence
The air-tightness of other branch air bags 13, still is able to play decelerating effect, to increase the safety of AD Aerodynamic Decelerator.Most preferably
Ground, inflating port are arranged on the leeward of lower second air bag, so that inflating port is closer to the high-pressure aerated bottle being located on rocket body.Separately
Outside, in gas replenishment process, the inflating port at symmetric position is needed while being inflated, it is ensured that in gas replenishment process, the second air bag is also protected
Hold symmetric profile.
It further include the multiple flexible character of flexible ribs being located in the second air bag for the aerodynamic stability for further improving the second air bag
14.For example, flexible character of flexible ribs 14 is in a ring, flexible character of flexible ribs 14 is threaded through in the second air bag along the circumferential direction of the second air bag, an annular
When the flexible character of flexible ribs 14 of multiple annulars across all air bags 13, can be arranged in flexible character of flexible ribs, multiple flexible character of flexible ribs 14 are second
Arranged stacked in the axial direction of air bag realizes the supporting role to the second air bag, and the shape after the second air bag is inflated is protected
It holds symmetrically, and the impact force for being able to bear the external world is bigger, aerodynamic stability is more preferable.
Alternatively, for another example, in all flexible character of flexible ribs 14, flexible character of flexible ribs 14 is in a ring, wherein the flexibility being located at head 11
Rib 14 is in circular ring shape；It is trapezoidal to stand upside down to be located at the longitudinal section shape of the flexible character of flexible ribs 14 on reverse taper 12, due to reverse taper
12 longitudinal section shape be stand upside down it is trapezoidal so that longitudinal section shape be stand upside down trapezoidal flexible character of flexible ribs 14 can with
The structure of cone is more identical, and the setting of flexible character of flexible ribs is played a supporting role while not changing pneumatic this body structure of head.Or
Flexible character of flexible ribs 14 of different shapes can also be individually located in a branch air bag 13, individually to play branch to each air bag 13
Support effect, further makes the shape of air bag controllable, and in entire moderating process, is able to maintain the symmetrical structure of pneumatic head 1
And aerodynamic stability.
Alternatively, flexible character of flexible ribs 14 is set directly between the windward side and leeward of each air bag 13, as shown in figure 5,
The shape of flexible character of flexible ribs does not limit.For example, flexible character of flexible ribs is in cylindrical body or plate.Flexible character of flexible ribs generally uses finer wire shape
At, or other materials, there is certain rigidity to play the second air bag of support while only there need to be flexibility and makes the second air bag
Symmetrical structure is kept, is also able to maintain symmetry when by foreign impacts power.The setting of flexible character of flexible ribs, the second air bag of enhancing are born
Ground shock has good aerodynamic configuration so that the aerodynamic stability of entire second air bag is high.
Alternatively, " the fixed seam " between above-mentioned two neighboring branch air bag 13 is tightly connected by flexible character of flexible ribs, it can not
Flexible character of flexible ribs is set in each air bag, can also play a supporting role to the second air bag and reinforces the effect of its intensity.
Second air bag mainly realizes the transformation between rounding state and unfolded state, air charging system by air charging system
It can be the high pressure gas cylinder being fixed on rocket body 6, the gas outlet of high pressure gas cylinder is connect with inflating port；Alternatively, air charging system includes
High-pressure aerated bottle and compressor, high pressure gas cylinder and compressor cooperation under, to be inflated to branch air bag 13, group level structure not into
Before entering atmosphere, branch air bag 13 is inflated using high pressure gas cylinder, after group level structure enters atmosphere, is filled using compressor
Gas, or tonifying Qi is carried out to high pressure gas cylinder using compressor, process is still inflated to branch air bag 13 using high pressure gas cylinder, from
And the second air bag is made to be switched to unfolded state from rounding state；On the contrary, when needing for gas in the second air bag to be discharged, it can be with
Oppositely the gas in the second air bag is withdrawn into high pressure gas cylinder, or is equipped with exhaust outlet on the second air bag, by the second gas
Intracapsular gas discharge, to realize that the second air bag is switched to rounding state from unfolded state, accordingly be equipped with can for exhaust outlet
Releasably sealing cover.
Rigid connector 2 is telescopically located on rocket body 6 by telescopic component, and as shown in Figure 7 and Figure 8, telescopic component includes
Multiple telescopic rods, multiple telescopic rods are uniformly distributed along the circumferential direction of rigid connector 2, and one end of telescopic rod and rigid connector 2 connect
It connects, the other end is connect with the head of rocket body 6.
For each telescopic rod, as shown in figure 8, each telescopic rod includes the first bar 41, the second bar 42 and snap lock
Tight part 43, the both ends of the first bar 41 to be expressed as first end and second end respectively, by the both ends of the second bar 42 point convenient for indicating
It is not expressed as third end and the 4th end.The first end of first bar 41 is fixed on rigid connector 2, such as solid using articulated manner
Fixed, in the second end of the first bar 41, the 4th end of the second bar 42 is fixed on rocket body 6 the third end cap of the second bar 42, such as
Also it is fixed using articulated manner.
First bar 41 and the second bar 42 be arranged after can be arranged on the side wall of the second bar 42 multiple in the position of overlapping region
First aperture 421 at interval, radially protruding is equipped with resilient latching member 43, such as resilient latching member 43 in the outside wall surface of the first bar 41
For elastic bumps or plunger, when the first bar 41 is driven under the driving of power (hereinafter referring to), the first bar 41 is directed away from second
The movement of 42 direction of bar, resilient latching member 43 is compressed and is slided in the second bar 42 at this time, when the first bar 41 is protruding in place
When, resilient latching member 43 is located just at one first and opens at 421 holes at this time, and resilient latching member 43 is popped up in release decrement
In first aperture 421, so that the first bar 41 and the second bar 42 be locked.
Optionally, it in order to enhance 42 connectivity robustness of the first bar 41 and the second bar, is arranged in the axial direction of the first bar 41 more
A resilient latching member, when the first bar 41 slides in place, resilient latching member is popped up correspondingly in the first aperture；Or also
Multiple resilient latching members can be arranged in the circumferential direction of the first bar 41, and multiple first apertures are arranged in the circumferential direction on the second bar 42,
Thus come the connectivity robustness for reinforcing the first bar 41 and the second bar 42.
In addition, aerodynamic decelerator mechanism further includes pack 5, before the second air bag unaerated, pack 5 is solid by blasting bolt
It is scheduled on the head of rocket body 6, the head of general rocket body is equipped with cabin, receiving cavity is formed between the cabin and pack, after gathering
The second air bag be loaded into pack 5.When needing the second airbag deployment, blasting bolt first explodes, and blasting bolt releases pack
With the coupling mechanism force between rocket body front end, high pressure gas cylinder on rocket body discharges high pressure gas later, the drive of high-pressure gas pack with
The front end of rocket body separates, or draws pack by setting mouse, separates pack and the front end of rocket body 6, pack 5 and the
By a traction element connection between two air bags, for example traction element is the steel wire of flexible high-temperature resistant, and pack 5 is to far from rocket body
When 6 stretching, apply driving force to the second air bag, and then the second air bag and rigid connector 2 is driven to pull up from the head of rocket body 6
Out, while rigid connector 2 is protruding, drive the first bar 41 protruding, so that telescopic rod is in stretching state；
Accordingly air charging system is to charge air conditioning in each air bag 13, so that the second air bag is from the gathering of starting and is accommodated in umbrella
The state of packet 5, is switched to unfolded state.Alternatively, pack can be replaced with to high pressure sleeve.
Pneumatic anticollision mechanism, which has, to be suitable for being located on the tail portion of rocket body 6, and can be between rounding state and unfolded state
Inflatable first air bag 7 of transformation, that is, the sunk area that the leeward of the first air bag 7 surrounds, the first air bag 7 is being unfolded
Suitable for covering on outside the tail portion of rocket body when state.In the present embodiment, the structure of the first air bag 7 is identical as the structure of the second air bag, no
It is only that with place: since the first air bag 7 is to play the role of buffering when rocket body lands, being not at hot environment, thus the
The outside wall surface of one air bag 7 no setting is required thermal insulation layer and burn-out proof layer, other structures and the structure of the second air bag are all the same, the first gas
Capsule 7 is also to be connect by rigid connector and telescopic component with rocket body, above-mentioned adjustment component is also provided on rocket body, to the first gas
The posture of capsule 7 is adjusted, and related content refers to the presentation content of the second air bag, and details are not described herein.Most preferably, the first gas
Capsule 7 and the second air bag are arranged symmetrically on rocket body.
The sub- level structure of this embodiment, firstly, thermal insulation layer 31 and burn-out proof layer 32 are set on second gasbag ektexine face, by
In burn-out proof layer other than its heat-proof quality, due also to it can absorb a large amount of heat in vaporization, to reduce the second air bag institute
The temperature for locating environment can also take away certain heat even if burn-out proof layer burns, and reduce the temperature of the second air bag local environment
Degree, enables the second air bag in altitude high temperature environment in use, the second air bag will not be burned out, the second air bag can be right
Rocket body 6 slows down；Secondly, the second air bag is arranged to symmetrical big blunt nosed, and flexible character of flexible ribs 14 is set in the second air bag,
So that the second air bag resistance to external shocks is strong and aerodynamic stability, the position that the second air bag lands is in controlled range；Later,
For two air bags before being not used, the second air bag is in rounding state and is incorporated in pack 5, reduces weight and the institute of deceleration device
The volume of occupancy keeps its compact-sized；It in 6 reentry of rocket body and lands during the entire process of ground, need to only be arranged one
Altitude high temperature, which can be completed, in a aerodynamic decelerator mechanism slows down and gentle aims at land；Since pneumatic anti-collision structure is arranged, so that rocket body
Tail portion land when, the first air bag 7 inflation after buffer function is played to the tail portion of rocket body so that the tail portion of rocket body can directly be hit
Hit and the tail portion of rocket body avoided to damage on the ground so that the sub- level structure realize AD Aerodynamic Decelerator it is flexible, foldable,
Thermal protection, high temperature resistant, the integrated setting of aerodynamic stability and tail portion landing anticollision.
As first interchangeable embodiment of embodiment 1, adjusting component may be replaced with other structures, than
Such as, adjustment component includes the first magnetosphere being located between the second gasbag ektexine face and thermal insulation layer 31, using permanent magnet material system
At the second magnetic substance being located on rocket body 6, the second magnetic substance is made of soft magnetic materials, is given the second magnetic substance indirect current, is made
It obtains the second magnetic substance and generates polarity, for example, logical positive electricity, the second magnetic substance are the pole S towards first magnetospheric one end polarity, lead to
Reversed electricity, the second magnetic substance is the pole N towards the first magnetospheric polarity, so that the second magnetic substance generates outward the second air bag
Repulsive force or adsorption capacity, to be adjusted come the expansion posture to the second air bag.In actual use, second is also set up
The gesture detector of air bag flight course, such as camera to be become according to the posture for obtaining the second air bag of taking pictures as further
Shape can also be not provided with above-mentioned adjustment component.
As second interchangeable embodiment of embodiment 1, the telescopic rod in telescopic component can be other quantity,
For example telescopic rod is one, two, three, four etc., when a telescopic rod is arranged, the first end of the first bar of telescopic rod is straight
It connects and is fixed on the end of rigid connector 2；When multiple telescopic rods are arranged, multiple telescopic rods are arranged in the outer of rigid connector 2
Week, so that rigid connector 2 is telescopic simultaneously with respect to rocket body 6, it is bigger to the supporting role of rigid connector 2, in turn
So that the posture of the second air bag is maintained at required symmetry status；Telescopic rod may be replaced with elastomeric element, such as spring.
The both ends of spring are connected to rigid connector 2 and rocket body 6, or as deformation, can also be not provided with telescopic component.
As the interchangeable embodiment of third of embodiment 1, flexible character of flexible ribs 14 can also be not provided with, at this time the second gas
Capsule relies primarily on the symmetry of own profile and the effect of high pressure gas, so that the second air bag keeps aerodynamic stability.
As the 4th interchangeable embodiment of embodiment 1, the second air bag can also be in an entirety, be not provided be in
Multiple air bags 13 can symmetrically set inflating port on the second air bag, be inflated simultaneously to the second air bag using two high pressure gas cylinders,
Guarantee the symmetry of the second air bag.
As the 5th interchangeable embodiment of embodiment 1, head 11 can not be in spherical crown shape, for example, head 11
In the shape of sub warhead；Alternatively, pneumatic head 1 is in revolving body, the diameter of the second air bag is along its axial direction by windward side towards leeward
Direction is gradually increased, and when the second airbag deployment state can also make the second air bag in symmetrical structure, so that the second air bag keeps good
Good aerodynamic stability.Similarly, the structure of the first air bag is similar with the structure of the second air bag, and details are not described herein, refers to
The structure of second air bag, but the outside wall surface of the first air bag no setting is required above-mentioned thermal insulation layer and burn-out proof layer.
As the 6th interchangeable embodiment of embodiment 1, it can also be not provided with above-mentioned thermal insulation layer, only setting is anti-
Ablation.
Embodiment 2
The present embodiment provides a seed level structure, the difference with the sub- level structure provided in embodiment 1 is only that: the first gas
The structure of capsule is different, and the pneumatic anticollision mechanism in the present embodiment can be with the air bag of other shapes, such as U-shaped air bag, S type gas
The air bag of capsule, V-type air bag or other shapes is ok, which can be located on the tail portion of rocket body, and rocket body is avoided to land
When, the tail portion of rocket body directly makes impact with the ground.
Obviously, the above embodiments are merely examples for clarifying the description, and does not limit the embodiments.It is right
For those of ordinary skill in the art, can also make on the basis of the above description it is other it is various forms of variation or
It changes.There is no necessity and possibility to exhaust all the enbodiments.And it is extended from this it is obvious variation or
It changes still within the protection scope of the invention.
Claims (10)
1. a seed level structure, which is characterized in that including
Rocket body (6)；
Pneumatic anticollision mechanism is located on the rocket body and inflatable with that can convert between rounding state and unfolded state
First air bag (7)；
Aerodynamic decelerator mechanism is located on the rocket body (6) comprising
Pneumatic head (1), for inflatable second air bag that can be converted between rounding state and unfolded state；Second air bag
In the unfolded state in the diameter of rotational-like and described second air bag along its axial direction by the windward side direction of the second air bag
The leeward direction of second air bag is gradually increased；
At least one layer of burn-out proof layer (32), is located in the outside wall surface of the second air bag；
First air bag (7) and the second air bag are suitable for being located at tail portion and the head of the rocket body (6) respectively in unfolded state
Outside portion.
2. sub- level structure according to claim 1, which is characterized in that the aerodynamic decelerator mechanism further includes being located at described
At least one layer of thermal insulation layer (31) between two gasbag ektexine faces and the burn-out proof layer (32).
3. sub- level structure according to claim 1 or 2, which is characterized in that second air bag includes head (11) and sets
Reverse taper (12) on the end of the head (11), the bus of the head (11) are smooth curve.
4. sub- level structure according to claim 3, which is characterized in that the head (11) is in spherical crown shape.
5. sub- level structure described in any one of -4 according to claim 1, which is characterized in that second air bag and the/the first gas
Capsule (7) includes at least two air bags (13) being circumferentially sequentially connected end to end along it；
Two neighboring branch air bag (13) sealing separates, and each branch air bag (13) is equipped with inflating port.
6. sub- level structure according to claim 5, which is characterized in that two branch air bags (13) of arbitrary neighborhood are each by being located at
Flexible character of flexible ribs (14) from first air bag (7) at place or in the second air bag seals partition；Or
At least one flexible character of flexible ribs (14) is provided in any air bag (13)；Alternatively, setting in the first air bag or the second air bag
There is at least one flexible character of flexible ribs (14), the circumferential direction of air bag of the flexible character of flexible ribs (14) along respective place crosses over all branch gas
Capsule (13).
7. sub- level structure according to claim 6, which is characterized in that be provided at least one when any air bag (13) is interior
Flexible character of flexible ribs (14)；Alternatively, being provided at least one flexible character of flexible ribs (14), the flexible character of flexible ribs in the first air bag or the second air bag
(14) when crossing over all air bag (13) along the circumferential direction of respective place air bag, the flexible character of flexible ribs (14) is at least two, is owned
The flexible character of flexible ribs (14) is in arranged stacked on corresponding air bag along the axial direction of respective place air bag.
8. sub- level structure described in any one of -7 according to claim 1, which is characterized in that first air bag (7) and/or
Second air bag is by the rigid connector (2) that is inlaid in the sunk area that respective leeward surrounds to be fixed on the rocket body
(6) on；
Second air bag or the first air bag (7) are suitable for covering corresponding rigid connector (2).
9. sub- level structure according to claim 8, which is characterized in that the rigid connector (2) passes through telescopic component edge
The axial direction of air bag is telescopically located on rocket body (6) where respectively.
10. sub- level structure according to claim 1 to 9, which is characterized in that first air bag (7) is in institute
When stating unfolded state in the diameter of rotational-like and described first air bag (7) along its axial direction by the windward side of the first air bag towards the
The leeward direction of one air bag is gradually increased.
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