CN109455318A - A kind of gas-filled unfolded re-entry deceleration system - Google Patents
A kind of gas-filled unfolded re-entry deceleration system Download PDFInfo
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- CN109455318A CN109455318A CN201811182967.0A CN201811182967A CN109455318A CN 109455318 A CN109455318 A CN 109455318A CN 201811182967 A CN201811182967 A CN 201811182967A CN 109455318 A CN109455318 A CN 109455318A
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- inflation ring
- gas
- cone
- section structure
- deceleration system
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
Abstract
A kind of gas-filled unfolded re-entry deceleration system, comprising: section structure, inflation ring, solar heat protection nose cone；Carry external load, the fixed solar heat protection nose cone in the head of the section structure in the inside of the section structure；The section structure is fixed with external satellite platform；The inflation ring is internal gassy airbag structure, and the multiple inflation ring, which is sequentially connected, is arranged in cone-shaped component, and the inflation ring positioned at cone-shaped component head is fixed with the solar heat protection nose cone, and the opening of the cone-shaped component is towards the section structure.It is of the invention that reenter return system light-weight, it occupies little space, it may be implemented to reduce construction weight and emit the requirement of volume and launch cost can be lowered, while the Aerodynamic Heating reentered in return course can be substantially reduced, expanded conventional aerospace device recycling landing technology and its application field.
Description
Technical field
The present invention relates to a kind of gas-filled unfolded re-entry deceleration systems, belong to Spacecraft Recovery and landing technical field.
Background technique
Conventional aerospace device re-entry deceleration and landing means include: 1) lift formula reenter return；2) engine work is pushed away using counter
Make the repulsion power generated to slow down；3) aerodynamic configuration deceleration+parachuting way of recycling.3rd kind of mode is current big applied to having
The main way that the Spacecraft reentry in compression ring border slows down with landing, reliability is higher, past using the spacecraft of this ways of deceleration
Toward having rigid solar heat protection outsole, it is able to bear and reenters Aerodynamic Heating high in return course, after speed is reduced to a certain extent,
Parachute is unfolded, parachuting deceleration is carried out to spacecraft and with the landing of the speed of safety.
The spacecraft of echo plex mode is reentered using aerodynamic configuration+parachuting, thermal protection struc ture is generally coated on spacecraft rigidity
Outside metal structure, quality is larger and occupies biggish space, for example, the payload that China's retrievable satellite can recycle
Weight accounts for 20%~30%, generally accounts for about recycling to the parachuting recovery system that spacecraft slows down reentering return latter stage work
10% or so of weight, therefore, this return efficiency for reentering echo plex mode are lower, change and traditional reenter echo plex mode, drop
The weight of low solar heat protection and rigid structure for improve star ship reenter return efficiency it is most important.
Summary of the invention
Technical problem solved by the present invention is overcome the deficiencies in the prior art, proposes gas-filled unfolded reenter of one kind and subtracts
Speed system changes traditional re-entry deceleration system using the working method of rigid thermal protection struc ture+parachute system, by above-mentioned apparatus
It is integrated into flexible thermal protection structure, on the basis of having solar heat protection and deceleration, foldable receipts when transmitting and before re-entry deceleration
Hold together inside spacecraft, effectively reduce storage space and launch cost, structure is simple, integrated level is higher.
The technical scheme is that
A kind of gas-filled unfolded re-entry deceleration system, comprising: section structure, inflation ring, solar heat protection nose cone, air charging system, fire
Work cutter, package rope, flexible heat shield；
Carry external load, the fixed solar heat protection nose cone in the head of the section structure in the inside of the section structure；The cabin
Body structure is fixed with external satellite platform；
The inflation ring is internal gassy airbag structure, and the multiple inflation ring is sequentially connected the tapered structure of arrangement
Part, the inflation ring positioned at cone-shaped component head are fixed with the solar heat protection nose cone, and the opening of the cone-shaped component is described in
Section structure.
The airbag structure of the inflation ring is solid made of being rotated a circle as a circle along an axis outside circle described in this
Structure, the outer axis of the circle are the central axis of the stereochemical structure；The central axis of the multiple inflation ring；
The inflation ring uses overlay film aramid fiber material, and the value range of the circle diameter d of inflation ring airbag structure is
200-400mm, the track of the circle center of circle rotation of the inflation ring airbag structure are the center radius R of inflation ring, the center
The value range of radius is 0.6m-6m；The number value range of the multiple inflation ring is 3 to 6.
The air charging system is placed on the inside of the section structure, for inflating to the multiple inflation ring.
Firer's cutter is fixed on section structure outer wall；The inflation ring, which folds, before inflation collapses in the cabin
On the outer wall of structure, and fixation is tied up using the package rope；When the air charging system needs to inflate to the inflation ring, institute
It states the power-up actuation of firer's cutter to cut off the package rope, the inflation ring is unfolded freely.
The flexibility heat shield is the stressed-skin construction of cone, and the stressed-skin construction is enclosed in the multiple inflation ring successively
It connects outside the cone-shaped component being arranged in.
The semi-cone angle value range of the flexibility heat shield cone is 45 °~60 °, frustum maximum radius rhDetermination side
Method, specifically:
Wherein, C is resistance coefficient, m be the inflatable re-entry deceleration system and its external load carried quality it
It is acceleration of gravity with, g, ρ is atmospheric density, and v is the landing speed of the inflatable re-entry deceleration system.
The solar heat protection nose cone semi-cone angle θcValue range be 45 °~60 °, the head of the solar heat protection nose cone passes through bulb knot
Structure Passivation Treatment, the value range of the dullness d are 0.15~0.25, the dullness d, specifically:
D=rN/rP,
rP=hsin θC
Wherein, rNFor the radius of the ball head structure, rPFor the maximum radius of the solar heat protection nose cone, h is the ball head structure
Height h.
The flexibility heat shield successively includes heat shield, heat insulation layer, bearing layer from outside to inside；The heat shield is high temperature resistant
Ceramic fiber fabric material；The heat insulation layer is inorganic thermal insulation composite material；The bearing layer uses fabric.
Molding is connected by way of sewing between each layer of the flexibility heat shield.
The air charging system is nitrogen, the volume V filled with gas in air charging system using pressure type inflation, working media is fallenq,
Specifically:
Wherein, PqFor the blowing pressure of the air charging system, PhFor the operating pressure of the inflation ring, TqFor the inflation
Temperature when device is inflated, ThFor the highest operating temperature of the inflation ring, VhFor needed for the multiple inflation ring gassy
Gas volume.
Compared with the prior art, the invention has the advantages that:
(1) present invention replaces traditional rigid thermal protection structure using flexible thermal protection structure, and density is no more than rigidity
The weight of system is greatly saved in the 30% of thermal protection structure；
(2) present invention can be greatlyd save using flexible thermal protection structure and airbag structure in launching phase FOLD AND PACK
Emission space；
(3) after the flexible heat shield 2 and 3 structure of inflation ring that the present invention uses are unfolded, aerodynamic decelerator can be played the role of,
Traditional parachuting recovery system can be saved, system is more simple, reliable；
(4) 3 structure of flexible gas-filled ring that the present invention is unfolded has both the effect of landing cushion gasbag and floatation pod, it can be achieved that multiplicity
Change function, the functions expanding for reentering return system is more preferable.
Detailed description of the invention
Fig. 1 is deceleration system course of work schematic diagram of the present invention；
Fig. 2 is deceleration system folded state structural schematic diagram of the present invention；
Fig. 3 is deceleration system unfolded state structural schematic diagram of the present invention；
Fig. 4 is 5 structural parameters schematic diagram of solar heat protection nose cone of the present invention；
Fig. 5 is that each inflation ring 3 of the present invention is connected fixed form schematic diagram；
Fig. 6 is that the present invention is connected and fixed button loop form schematic diagram；
Fig. 7 is 6 structural schematic diagram of firer's cutter of the present invention.
Specific embodiment
It is as shown in Figure 1 a kind of inflatable re-entry deceleration system operation programs schematic diagram of the present invention.Inflatable re-entry deceleration
System is connected and fixed by standard interface provided by space station or spacecraft platform and stores storage, and system, which is in, at this time folds
Packed state, launches and in orbit with spacecraft platform.When needing to reenter return from track, passed through by spacecraft platform
Automated manner or spacefarer's manual operation discharge inflatable re-entry deceleration system (containing external payload) from platform, and
Entered afterwards by vehicle out-driving and reenter return trajectory, and carried out quickly space track (orbit altitude is generally 120~160km)
Inflating expanded, inflationtime is usually no more than 50s, be fully deployed after as shown in figure 3, using expansion after coniform aerodynamic configuration into
Row aerodynamic decelerator, flexible heat shield 2 bear the Aerodynamic Heating reentered in return course, and final safe landing ground or splash down floats on
Sea, landing speed are usually no more than 30m/s.
A kind of gas-filled unfolded re-entry deceleration system, comprising: section structure 1, flexible heat shield 2, inflation ring 3, inflation dress
Set 4, solar heat protection nose cone 5, firer's cutter 6, package rope 7；
Carry external load, the fixed solar heat protection nose cone 5 in the head of the section structure 1 in the inside of the section structure 1；It is described
Section structure 1 is fixed with external satellite platform；
The inflation ring 3 is internal gassiness airbag structure, full of being can use in annulus utricule structure after gas
External differential bears the aerodynamic loading generated in flight course, keeps stable aerodynamic configuration, provides pneumatic needed for aerodynamic decelerator
Resistance.The airbag structure is stereochemical structure made of being rotated a circle as a circle along an axis outside circle described in this, the circle
Enclose the central axis that an outer axis is the stereochemical structure；The multiple center radius inflation ring 3 of different sizes presses radius size
It is sequentially connected from small to large and is arranged in cone-shaped component, the central axis of the multiple inflation ring 3；It is described to be located at cone-shaped component head
The inflation ring 3 in portion and the solar heat protection nose cone 5 are fixed, and the opening of the cone-shaped component is towards the section structure 1.
The inflation ring 3 uses overlay film aramid fiber material, the value range of the circle diameter d of 3 airbag structure of inflation ring
For 200~400mm, the track of the circle center of circle rotation of 3 airbag structure of inflation ring is the center radius R of inflation ring 3, described
The value range of center radius is 0.6m~6m；The number value range of the multiple inflation ring 3 is 3 to 6.
The air charging system 4 is placed on the inside of the section structure 1, for inflating to the multiple inflation ring 3；Outlet
Mouth is more inflated hoses, and intake valve 10 is provided on inflation ring 3, connect with inflated hose and reliably seals.Air charging system 4
Including high pressure gas cylinder, electric blasting valve (or latching valve), decompression device, loading line, inflating gas cylinder valve, inflated hose etc., gas cylinder pressure
Power is usually no more than 35MPa.The inflation ring 3 of the unaerated, which folds, to be collapsed on the outer wall of section structure 1, and uses package rope
7 tie up fixation, and after Spacecraft reentry to low rail, the section structure 1 is separated with the satellite platform, when section structure 1
When orbit altitude and the angle of attack meet design objective simultaneously, firer's cutter 6 is powered on actuation and cuts off the package rope 7, makes to inflate
After ring 3 is freely unfolded, air charging system 4 is inflated to the multiple inflation ring 3, until the multiple inflation ring 3 is fully deployed to be formed
Cone-shaped component, as shown in Figure 3.
Firer's cutter 6 is fixed on 1 outer wall of section structure；The package rope 7 is by the inflation ring 3 of the unaerated
It folds and is collapsed on the outer wall of the section structure 1 as shown in Figure 2, it is described before the air charging system 4 gives the inflation ring 3
Firer's cutter 6 is powered on actuation and cuts off the package rope 7, and the inflation ring 3 is unfolded freely.As shown in fig. 7, for the present invention
A kind of firer's cutter 6 of inflatable re-entry deceleration system, firer's cutter 6 use electric initiating form, pass through its flange auricle
It is installed on 1 outer wall of section structure, cuts package rope 7 across firer when inflation ring 3 and the flexible completion of heat shield 2 FOLD AND PACK
The lacing hole of device 6, actuation after firer's cutter 6 is powered, the package rope 7 at lacing hole is cut off, the constraint of folded formation is released.
It is described flexibility heat shield 2 be cone stressed-skin construction, the stressed-skin construction be enclosed in the multiple inflation ring 3 according to
It is secondary to connect outside the cone-shaped component being arranged in.Flexible heat shield 2 is connected and fixed by button loop and rope band binding.
It is as shown in Figure 5 and Figure 6 a kind of fixed form signal of inflation ring 3 of inflatable re-entry deceleration system of the present invention
Figure.Each inflation ring 3 ties up fixation by radial belt 9 and around band 8, wherein around band 8 for carrying out between adjacent inflation ring 3
Bundled fixed, the main function of radial belt 9 are that inflation ring 3 is fixedly connected on section structure 1, do not allow inflation ring 3 to be scattered, together
When and prevent inflation ring 3 from misplace during the work time movement around band 8, the global shape of cone, radial belt 9 and cabin are inflated in maintenance
The button loop connection being arranged in body structure 1.Radial belt 9 and the material for surrounding band 8 generally use aramid belt.
Multiple column button loops are set between two neighboring inflation ring 3, in the tangent position of section circle, is passed through by rope band and buckles loop
Two inflation rings 3 are reliably connected fixation, flexible heat shield 2 and 3 section of each inflation ring circle tangency location are equally arranged button loop, lead to
It crosses rope band and passes through and buckle loop and be reliably connected the two.
The semi-cone angle value range of 2 cone of flexibility heat shield is 45 °~60 °, frustum maximum radius rhAccording to winged
The landing speed of row device determines.Frustum maximum radius rhDetermination method, specifically:
Wherein, C is resistance coefficient, m be the inflatable re-entry deceleration system and its external load carried quality it
It is acceleration of gravity with, g, v is the landing speed of the inflatable re-entry deceleration system, and ρ is atmospheric density, big by room temperature standard
Under air pressure, ρ=1.225kg/m3。
The flexibility heat shield 2 successively includes heat shield, heat insulation layer, bearing layer from outside to inside；The heat shield is resistance to height
Warm ceramic fiber fabric material, for obstructing Orbital heat flux；The heat insulation layer be inorganic thermal insulation composite material, for trap heat to
Transmitting inside heat shield；The bearing layer makes the multiple inflation for bearing the load in flight course using fabric
Ring 3 keeps cone-shaped component.Molding is connected between each layer by way of sewing；
As shown in figure 4, the 5 semi-cone angle θ of solar heat protection nose conecValue range be 45 °~60 °, the head of the solar heat protection nose cone 5
Portion is by ball head structure Passivation Treatment, and the value range of the dullness d is 0.15~0.25, preferred d=2, the dullness d,
Specifically:
D=rN/rP,
rP=hsin θC,
Wherein, rNFor the radius of the ball head structure, rPFor the maximum radius of the solar heat protection nose cone 5, h is the bulb knot
The height h of structure.
Solar heat protection nose cone 5 is using rigid ablator, such as quartz phenolic material.
Air charging system 4 is using pressure type inflation is fallen, and working media is nitrogen, and the gas pressure of 4 high pressure gas cylinder of air charging system takes
It is worth range and is not more than 35MPa, the volume V filled with gas in air charging system 4, specifically:
Wherein, PqFor the blowing pressure of the air charging system 4, PhFor the operating pressure of the inflation ring 3, PhValue model
It encloses for 80~150KPa, TqTemperature when to be inflated to 4 high pressure gas cylinder of air charging system, TqValue range be 18~30 DEG C, preferably
It is room temperature, ThFor the highest operating temperature of the inflation ring 3, VhFor gas body needed for the multiple 3 gassy of inflation ring
Product.
Flexible heat shield 2 and inflation ring 3 enter the orbit in Spacecraft Launch and in orbit the stage be in FOLD AND PACK state, receive
Hold together around section structure 1 (or external payload), meets Spacecraft Launch space requirement, FOLD AND PACK density is not generally small
In 0.2kg/L.Inflation ring 3 and flexible heat shield 2 after gathering are packed into inside package and by the constraints of package rope 7, fixed, package
Rope 7 passes through the lacing hole for the rope cutter that closes up, and when cutter actuation, cutter can cut off the package rope 7 at lacing hole, thus
Release package constraint.1 outer wall of section structure is provided with press strip, the press strip link of flexible heat shield 2 and section structure 1 is fixed.
When system satisfaction reenters return condition (0~5 ° of return altitude 120km~160km, the angle of attack), package is cut off in cutter actuation
Rope 7 releases the constraint of inflation ring 3 and flexible heat shield 2, after several seconds, starts air charging system 4, is quickly filled with to 3 inside of inflation ring
Nitrogen, multi-turn inflation ring 3 are orderly unfolded, and inflationtime is usually no more than 50s, and inflation ring 3 drives flexible heat shield 2 to open up simultaneously
It opens, wraps up section structure 1 after being fully deployed, form coniform aerodynamic configuration, slow down to spacecraft, while flexible solar heat protection
Cover 2 completes thermal protection function, and receiving reenters Aerodynamic Heating, protects section structure 1 and external payload from burning, inflation ring 3
System can be buffered when spacecraft lands, if spacecraft is overboard also to can be used as floatation pod, it be made to float on the water surface, be convenient for
Search is salvaged.
The content that description in the present invention is not described in detail belongs to the well-known technique of professional and technical personnel in the field.
Claims (10)
1. a kind of gas-filled unfolded re-entry deceleration system characterized by comprising section structure (1), inflation ring (3), solar heat protection head
It bores (5)；
External load is carried in the inside of the section structure (1), and the head of the section structure (1) is fixed solar heat protection nose cone (5)；Institute
Section structure (1) is stated to fix with external satellite platform；
The inflation ring (3) is internal gassiness airbag structure, and it is tapered that the multiple inflation ring (3) is sequentially connected arrangement
Component, the inflation ring (3) positioned at cone-shaped component head and the solar heat protection nose cone (5) are fixed, the opening of the cone-shaped component
Towards the section structure (1).
2. a kind of gas-filled unfolded re-entry deceleration system according to claim 1, which is characterized in that the inflation ring (3)
Airbag structure be stereochemical structure made of being rotated a circle as a circle along an axis outside circle described in this, the outer axis of the circle
Line is the central axis of the stereochemical structure；The central axis of the multiple inflation ring (3)；
The inflation ring (3) uses overlay film aramid fiber material, the value range of the circle diameter d of inflation ring (3) airbag structure
Track for 200~400mm, the circle center of circle rotation of inflation ring (3) airbag structure is the center radius R of inflation ring (3),
The value range of the center radius is 0.6m~6m；The number value range of the multiple inflation ring (3) is 3 to 6.
3. a kind of gas-filled unfolded re-entry deceleration system according to claim 1 or 2, which is characterized in that further include inflation
Device (4)；
The air charging system (4) is placed on the inside of the section structure (1), for inflating to the multiple inflation ring (3).
4. a kind of gas-filled unfolded re-entry deceleration system according to claim 3, which is characterized in that further include firer's cutting
Device (6), package rope (7)；
Firer's cutter (6) is fixed on section structure (1) outer wall；The inflation ring (3), which folds, before inflation collapses in institute
On the outer wall for stating section structure (1), and fixation is tied up using the package rope (7), when the air charging system (4) are needed to described
When inflation ring (3) is inflated, the package rope (7) is cut off in firer's cutter (6) power-up actuation, makes the inflation ring (3)
Freely it is unfolded.
5. a kind of gas-filled unfolded re-entry deceleration system according to claim 4, which is characterized in that further include flexible solar heat protection
It covers (2)；
It is described flexibility heat shield (2) be cone stressed-skin construction, the stressed-skin construction be enclosed in the multiple inflation ring (3) according to
It is secondary to connect outside the cone-shaped component being arranged in.
6. a kind of gas-filled unfolded re-entry deceleration system according to claim 5, which is characterized in that the flexibility heat shield
(2) conical semi-cone angle value range is 45 °~60 °, frustum maximum radius rhDetermination method, specifically:
Wherein, C is resistance coefficient, and m is the quality sum of the inflatable re-entry deceleration system and its external load carried, g
For acceleration of gravity, ρ is atmospheric density, and v is the landing speed of the inflatable re-entry deceleration system.
7. a kind of gas-filled unfolded re-entry deceleration system according to claim 6, which is characterized in that the solar heat protection nose cone
(5) semi-cone angle θCValue range be 45 °~60 °, the head of the solar heat protection nose cone (5) passes through ball head structure Passivation Treatment, institute
State dullness d value range be 0.15~0.25, the dullness d, specifically:
D=rN/rP,
rP=hsin θC,
Wherein, rNFor the radius of the ball head structure, rPFor the maximum radius of the solar heat protection nose cone (5), h is the ball head structure
Height h.
8. a kind of gas-filled unfolded re-entry deceleration system according to claim 5, which is characterized in that the flexibility heat shield
It (2) from outside to inside successively include heat shield, heat insulation layer, bearing layer；The heat shield is pyroceram fibre textile material；Institute
Stating heat insulation layer is inorganic thermal insulation composite material；The bearing layer uses fabric.
9. a kind of gas-filled unfolded re-entry deceleration system according to claim 8, which is characterized in that the flexibility heat shield
(2) molding is connected by way of sewing between each layer.
10. a kind of gas-filled unfolded re-entry deceleration system according to one of claim 4-9, which is characterized in that described to fill
Device of air (4) is nitrogen, the volume V filled with gas in air charging system (4) using pressure type inflation, working media is fallenq, specifically:
Wherein, PqFor the blowing pressure of the air charging system (4), PhFor the operating pressure of the inflation ring (3), TqIt is filled to be described
Temperature when device of air (4) is inflated, ThFor the inflation ring (3) highest operating temperature, VhIt is filled for the multiple inflation ring (3)
Gas volume needed for full gas.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811182967.0A CN109455318A (en) | 2018-10-11 | 2018-10-11 | A kind of gas-filled unfolded re-entry deceleration system |
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| CN201811182967.0A CN109455318A (en) | 2018-10-11 | 2018-10-11 | A kind of gas-filled unfolded re-entry deceleration system |
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| CN109855480A (en) * | 2019-04-02 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Solid Launch Vehicle grade recovery structure and ballistic, trajectory-lift formula Reentry vehicle |
| CN110116823A (en) * | 2019-04-19 | 2019-08-13 | 北京星际荣耀空间科技有限公司 | A kind of recyclable and multiplexing Solid Launch Vehicle grade |
| CN110435934A (en) * | 2019-07-19 | 2019-11-12 | 西北工业大学 | A kind of reusable inert satellite recovery flight device |
| CN110803303A (en) * | 2019-10-18 | 2020-02-18 | 北京空间机电研究所 | Inflatable deployable resistance-increasing off-rail structure |
| CN111017262A (en) * | 2019-11-28 | 2020-04-17 | 北京空间机电研究所 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
| CN113280694A (en) * | 2021-04-06 | 2021-08-20 | 北京空天技术研究所 | Integrated air bag speed reduction device for interstage separation of aircraft and design method |
| WO2023096820A3 (en) * | 2021-11-17 | 2023-10-26 | Outpost Technologies Corporation | Space vehicles with paraglider re-entry, and associated systems and methods |
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| CN111017262A (en) * | 2019-11-28 | 2020-04-17 | 北京空间机电研究所 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
| CN111017262B (en) * | 2019-11-28 | 2021-07-13 | 北京空间机电研究所 | Inflatable reentry deceleration flexible unfolding structure folding and unfolding method |
| CN113280694A (en) * | 2021-04-06 | 2021-08-20 | 北京空天技术研究所 | Integrated air bag speed reduction device for interstage separation of aircraft and design method |
| CN113280694B (en) * | 2021-04-06 | 2022-11-11 | 北京空天技术研究所 | Integrated air bag speed reduction device for interstage separation of aircraft and design method |
| WO2023096820A3 (en) * | 2021-11-17 | 2023-10-26 | Outpost Technologies Corporation | Space vehicles with paraglider re-entry, and associated systems and methods |
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Application publication date: 20190312 |