ITUA20164513A1 - USE OF A SILICA-BASED MATERIAL IN AEROSPACE APPLICATIONS - Google Patents
USE OF A SILICA-BASED MATERIAL IN AEROSPACE APPLICATIONS Download PDFInfo
- Publication number
- ITUA20164513A1 ITUA20164513A1 ITUA2016A004513A ITUA20164513A ITUA20164513A1 IT UA20164513 A1 ITUA20164513 A1 IT UA20164513A1 IT UA2016A004513 A ITUA2016A004513 A IT UA2016A004513A IT UA20164513 A ITUA20164513 A IT UA20164513A IT UA20164513 A1 ITUA20164513 A1 IT UA20164513A1
- Authority
- IT
- Italy
- Prior art keywords
- based material
- silica
- sio2
- articulated frame
- aerospace
- Prior art date
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- 239000000463 material Substances 0.000 title claims description 30
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 34
- 239000000377 silicon dioxide Substances 0.000 claims description 17
- 229910052681 coesite Inorganic materials 0.000 claims description 7
- 229910052906 cristobalite Inorganic materials 0.000 claims description 7
- 235000012239 silicon dioxide Nutrition 0.000 claims description 7
- 229910052682 stishovite Inorganic materials 0.000 claims description 7
- 229910052905 tridymite Inorganic materials 0.000 claims description 7
- 230000035882 stress Effects 0.000 description 5
- 239000000126 substance Substances 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 229920000271 Kevlar® Polymers 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 150000007513 acids Chemical class 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000004761 kevlar Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 238000002310 reflectometry Methods 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 238000000859 sublimation Methods 0.000 description 1
- 230000008022 sublimation Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- 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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Compositions Of Macromolecular Compounds (AREA)
- Silicon Compounds (AREA)
Description
“USO DI UN MATERIALE A BASE DI SILICE IN APPLICAZIONI AEROSPAZIALI” "USE OF A SILICA-BASED MATERIAL IN AEROSPACE APPLICATIONS"
La presente invenzione è relativa all’utilizzo di un materiale in applicazioni aerospaziali, quali ad esempio dispositivi di frenatura per corpi in fase di rientro sia in orbita terrestre che extraterrestre; strutture abitanti e non su siti extraterrestri; giunture e coperture per componentistica in ambito spaziale e aeronautico; coperture per rotori. The present invention relates to the use of a material in aerospace applications, such as for example braking devices for bodies in the re-entry phase both in terrestrial and extraterrestrial orbit; inhabiting and non-inhabiting structures on extraterrestrial sites; joints and covers for components in space and aeronautics; rotor covers.
Solitamente, le strutture che operano in ambito aerospaziale sono soggette a condizioni ambientali che possono risultare critiche a breve o a lungo termine e, di conseguenza, c’è la necessità di disporre di materiali in grado di garantire una adeguata resistenza a tale condizioni. In particolare, vi sono determinati componenti che più di altri sono soggetti alle condizioni critiche di cui sopra. Usually, structures operating in the aerospace sector are subject to environmental conditions that can be critical in the short or long term and, consequently, there is a need to have materials capable of ensuring adequate resistance to such conditions. In particular, there are certain components that more than others are subject to the aforementioned critical conditions.
Tali condizioni critiche possono ad esempio derivare dall’esposizione a temperature alte, come avviene in strutture soggette a forte riscaldamento aerodinamico o in prossimità dei propulsori o, ancora, per componenti spaziali esposti a continue sorgenti di energia (ad esempio solare o interna). Temperature troppo elevate possono provocare variazioni temporanee o permanenti delle caratteristiche fisiche e meccaniche dei materiali, accelerare reazioni di corrosione e ossidazione o indurre deformazioni e tensioni strutturali. Such critical conditions may, for example, derive from exposure to high temperatures, as occurs in structures subject to strong aerodynamic heating or in the vicinity of the thrusters or, again, for space components exposed to continuous sources of energy (for example solar or internal). Temperatures that are too high can cause temporary or permanent changes in the physical and mechanical characteristics of the materials, accelerate corrosion and oxidation reactions or induce structural deformations and stresses.
Inoltre, va ricordato che per strutture che operano in Orbita Terrestre Bassa, indicata con LEO (Low Earth Orbit) gli effetti dovuti all’ambiente spaziale sui materiali sono significativi. Tra questi effetti si ricordano in particolare i punti seguenti. In addition, it should be remembered that for structures operating in Low Earth Orbit, indicated with LEO (Low Earth Orbit), the effects due to the space environment on materials are significant. Among these effects, the following points are particularly worthy of note.
Il vuoto nello spazio: in orbita intorno alla Terra ed a grande distanza dalla Terra la pressione varia da: The vacuum in space: in orbit around the Earth and at a great distance from the Earth, the pressure varies from:
pleo = 1.3x10-7 KPa (a 200 Km di quota ) p6500 = 1.3x10-12 KPa (ad oltre 6500 Km di quota). pleo = 1.3x10-7 KPa (at 200 km of altitude) p6500 = 1.3x10-12 KPa (at over 6500 km of altitude).
In queste condizioni di pressione si possono presentare degli effetti significativi come la decomposizione di polimeri o la sublimazione (perdita di molecole) nei metalli. Significant effects such as decomposition of polymers or sublimation (loss of molecules) in metals can occur under these pressure conditions.
Infine, va anche considerato che a carichi termici elevati possono aggiungersi a forti sollecitazioni meccaniche o vibrazionali, come avviene ad esempio nei propulsori o nei veicoli spaziali. Finally, it should also be considered that high thermal loads can be added to strong mechanical or vibrational stresses, as occurs for example in propellers or spacecraft.
Ad oggi i materiali maggiormente utilizzati sono il titanio (Ti), l’alluminio (Al), le resine termoindurenti, i materiali ceramici, le fibre di carbonio, il kevlar e alcuni materiali compositi. To date, the most used materials are titanium (Ti), aluminum (Al), thermosetting resins, ceramic materials, carbon fibers, Kevlar and some composite materials.
I materiali sopra menzionati, nonostante riescano a garantire la resistenza richiesta, tuttavia soffrono lo svantaggio di essere estremamente pesanti e costosi e, di conseguenza, di risultare utilizzabili solo in situazioni estremamente di nicchia. The materials mentioned above, despite being able to guarantee the required resistance, nevertheless suffer the disadvantage of being extremely heavy and expensive and, consequently, of being usable only in extremely niche situations.
Inoltre, le leghe di acciaio, molto utilizzate in ambiente spaziale, possono creare problemi per la presenza di magnetometri a bordo dei satelliti, presentano lo svantaggio di avere un’alta densità, vanno soggetti a pericolo di infragilimento da idrogeno e hanno un peso elevato. In addition, steel alloys, widely used in the space environment, can create problems due to the presence of magnetometers on board the satellites, have the disadvantage of having a high density, are subject to the danger of hydrogen embrittlement and have a high weight.
Era quindi sentita l’esigenza di poter disporre in ambito aerospaziale di un materiale le cui caratteristiche tecniche fossero tali da garantire una elevata resistenza termica, chimica e meccanica e, al tempo stesso, risultassero di costo contenuto e, quindi, applicabili su larga scala. The need was therefore felt to be able to dispose of a material in the aerospace field whose technical characteristics were such as to ensure high thermal, chemical and mechanical resistance and, at the same time, were of low cost and, therefore, applicable on a large scale.
La Richiedente ha trovato un materiale che fino ad oggi è stato utilizzato in campi diversi dall’aerospazio, e che può soddisfare in maniera efficace le necessità di cui sopra. The Applicant has found a material that up to now has been used in fields other than aerospace, and which can effectively meet the above needs.
Oggetto della presente invenzione è l’uso in dispostivi e/o strutture in ambito aerospaziale di un materiale a base di silice caratterizzato dal fatto di (a) essere costituito almeno dal 85% in peso di SiO2; (b) avere una densità compresa tra 0,5 a 1,0 g/cm<3>; (c) avere una porosità compresa tra 50 e 80% in volume. The object of the present invention is the use in aerospace devices and / or structures of a silica-based material characterized by the fact of (a) consisting of at least 85% by weight of SiO2; (b) have a density ranging from 0.5 to 1.0 g / cm <3>; (c) have a porosity of between 50 and 80% by volume.
Preferibilmente, detto materiale a base di silice è costituito almeno dal 90% in peso di SiO2. Preferably, said silica-based material consists of at least 90% by weight of SiO2.
Preferibilmente, detto materiale a base di silice ha una densità compresa tra 0,7 e 0,9 g/cm<3>. Preferably, said silica-based material has a density of between 0.7 and 0.9 g / cm <3>.
Preferibilmente, detto materiale a base di silice ha una porosità compresa tra 60 e 70%. Preferably, said silica-based material has a porosity of between 60 and 70%.
Un ulteriore oggetto della presente invenzione è un dispositivo o una struttura aerospaziale comprendente il materiale a base di silice secondo la presente invenzione. A further object of the present invention is an aerospace device or structure comprising the silica-based material according to the present invention.
Di seguito è riportato un esempio realizzativo a puro titolo illustrativo e non limitativo con l’ausilio della figura allegata che illustra un dispositivo di frenatura e di protezione termica per corpi in fase di atterraggio. Below is an example of construction for illustrative and non-limiting purposes with the aid of the attached figure which illustrates a braking and thermal protection device for bodies in the landing phase.
Nella figura allegata è indicato nel suo complesso con 1 un dispositivo di frenatura e di protezione termica. In the attached figure, 1 indicates as a whole a braking and thermal protection device.
Il dispositivo 1 comprende un telaio articolato 2 mobile tra una sua configurazione chiusa e una sua configurazione aperta, uno scudo frenante 3 ripiegabile, fissato al telaio articolato 2 per ripiegarsi quando il telaio articolato 2 stesso è nella sua configurazione chiusa e distendersi quando il telaio articolato 2 è nella sua configurazione aperta e un azionatore centrale di apertura 4 atto a movimentare il telaio 2 The device 1 comprises an articulated frame 2 movable between its closed configuration and its open configuration, a folding braking shield 3, fixed to the articulated frame 2 to fold when the articulated frame 2 itself is in its closed configuration and to extend when the articulated frame 2 is in its open configuration and a central opening actuator 4 adapted to move the frame 2
Come è possibile rilevare dalla figura del disegno allegato, l’azionatore centrale di apertura 4 comprende una porzione frontale 5 a forma di calotta sferica. Come può risultare ovvio ad un tecnico del ramo, durante il funzionamento del dispositivo la porzione frontale è la parte maggiormente soggetta a stress termici, stress meccanici e stress chimici. As can be seen from the figure of the attached drawing, the central opening actuator 4 comprises a front portion 5 in the shape of a spherical cap. As may be obvious to a person skilled in the art, during the operation of the device the front portion is the part most subjected to thermal stress, mechanical stress and chemical stress.
Nel particolare esempio realizzativo la parte frontale 5 è stata realizzata con un materiale a base di silice secondo l’invenzione. In the particular embodiment example, the front part 5 was made with a silica-based material according to the invention.
In particolare, la parte frontale 5 è stata realizzata con un materiale commercializzato con il nome commerciale RESCOR 310M dalla società COTRONICS CORPORATION. Nello specifico il materiale utilizzato è composto dal 99% in peso da SiO2, ha una densità pari a 0,80 g/cm<3>e presenta una porosità pari al 63% in volume. In particular, the front part 5 was made with a material marketed under the trade name RESCOR 310M by the company COTRONICS CORPORATION. Specifically, the material used is composed of 99% by weight of SiO2, has a density of 0.80 g / cm <3> and has a porosity of 63% by volume.
È stato sperimentalmente dimostrato che l’utilizzo del materiale di cui sopra è in grado di garantire la resistenza della porzione frontale 5 del dispositivo 1 durante il suo utilizzo. Infatti, la porzione frontale 5 è risultata resistente agli stress termici, chimici e meccanici subiti. It has been experimentally shown that the use of the above material is able to guarantee the resistance of the front portion 5 of the device 1 during its use. In fact, the front portion 5 was found to be resistant to the thermal, chemical and mechanical stresses suffered.
Il materiale secondo la presente invenzione, grazie al suo prezzo contenuto e alle sue caratteristiche costituisce una valida e vantaggiosa alternativa ai materiali oggi impiegati per strutture spaziali ed aereonautiche. The material according to the present invention, thanks to its low price and its characteristics, constitutes a valid and advantageous alternative to the materials currently used for space and aeronautical structures.
Relativamente alle caratteristiche tecniche del materiale secondo la presente invenzione va, infatti, considerato che questo risulta estremamente leggero, sopporta temperature fino a 1650°C., è caratterizzato da un basso coefficiente di espansione termica e da un’elevata resistenza agli shock termici, ha una bassa conducibilità termica ma un’elevata riflettività, è resistente sia alle atmosfere ossidanti sia alle atmosfere riducenti, ai metalli fusi, al vapore, ai gas corrosivi, alla maggior parte degli acidi e dei solventi, non contiene sostanze organiche e non degassa nel vuoto. With regard to the technical characteristics of the material according to the present invention, it must be considered that it is extremely light, withstands temperatures up to 1650 ° C., Is characterized by a low coefficient of thermal expansion and by a high resistance to thermal shock, has low thermal conductivity but high reflectivity, it is resistant to both oxidizing and reducing atmospheres, molten metals, steam, corrosive gases, most acids and solvents, does not contain organic substances and does not degass in vacuum .
Infine, il materiale secondo la presente invenzione, per le sue caratteristiche, si presenta come una più valida e vantaggiosa alternativa anche nei confronti dei materiali compositi, molto costosi e troppo sensibili all’ossigeno atomico (tanto da richiedere l’impiego di strati protettivi per l’uso in ambienti spaziali). Finally, the material according to the present invention, due to its characteristics, is a more valid and advantageous alternative also towards composite materials, which are very expensive and too sensitive to atomic oxygen (so much so as to require the use of protective layers for use in space environments).
Infine, il materiale secondo la presente invenzione, se opportunamente combinato, può migliorare ulteriormente le sue caratteristiche in termini di resistenza meccanica e diminuzione di peso. In particolare, si fa riferimento ad un composito (FW12) fatto di fibre di nextel affogate in una matrice ceramica composta di ALLUMINA (85%) e 3YSZ (15%). Finally, the material according to the present invention, if suitably combined, can further improve its characteristics in terms of mechanical strength and weight reduction. In particular, we refer to a composite (FW12) made of nextel fibers embedded in a ceramic matrix composed of ALUMINA (85%) and 3YSZ (15%).
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ITUA2016A004513A ITUA20164513A1 (en) | 2016-06-20 | 2016-06-20 | USE OF A SILICA-BASED MATERIAL IN AEROSPACE APPLICATIONS |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ITUA2016A004513A ITUA20164513A1 (en) | 2016-06-20 | 2016-06-20 | USE OF A SILICA-BASED MATERIAL IN AEROSPACE APPLICATIONS |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| ITUA20164513A1 true ITUA20164513A1 (en) | 2017-12-20 |
Family
ID=57184720
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| ITUA2016A004513A ITUA20164513A1 (en) | 2016-06-20 | 2016-06-20 | USE OF A SILICA-BASED MATERIAL IN AEROSPACE APPLICATIONS |
Country Status (1)
| Country | Link |
|---|---|
| IT (1) | ITUA20164513A1 (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8733706B1 (en) * | 2012-05-15 | 2014-05-27 | The United States of America as represented by the Administrator of the National Aeronautics & Space Administration (NASA) | Transformable and reconfigurable entry, descent and landing systems and methods |
-
2016
- 2016-06-20 IT ITUA2016A004513A patent/ITUA20164513A1/en unknown
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8733706B1 (en) * | 2012-05-15 | 2014-05-27 | The United States of America as represented by the Administrator of the National Aeronautics & Space Administration (NASA) | Transformable and reconfigurable entry, descent and landing systems and methods |
Non-Patent Citations (2)
| Title |
|---|
| MATTHIAS WIEGAND ET AL: "A Small Re-entry Capsule -BREM-SAT 2", PROCEEDINGS OF THE 10TH AIAA/USU SMALL SATELLITE CONFERENCE, LOGAN, 1 January 1996 (1996-01-01), XP055224098, Retrieved from the Internet <URL:http://digitalcommons.usu.edu/cgi/viewcontent.cgi?article=2469&context=smallsat> [retrieved on 20151028] * |
| VALERIO CARANDENTE: "Aerothermodynamic and mission analyses of deployable aerobraking entry systems", PHD THESIS UNIVERSITÀ DEGLI STUDI DI NAPOLI FEDERICO II, 7 April 2014 (2014-04-07), XP055354519, Retrieved from the Internet <URL:http://www.fedoa.unina.it/9798/1/carandente_valerio_26.pdf> [retrieved on 20170314] * |
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