DE-ORBITING AND THERMAL PROTECTION GROUP FOR CUBESATS

Description

DESCRIPTION of the patent for Industrial Invention from the title: “ GRU PP ODIDE - ORBITINGPROTECTIONETE RMICADA APPLY AT QUICKLY ” by SPACEFACTORYSRL of Italian nationality concede : VTIAEMANUELEGIANTURCO , 3 1 - 8 0 1 4 6 NAPLES ( NA ) Inventors : Cranberry PUNZOF , Orberto SALZAN , Ring FUSCOD IF TT HEAR LL TECHNICAL The present invention relates to a group of - orbiting and thermal protection applicable to CubeSat. In particular, the present invention relates to a 15 set of de-orbiting and thermal protection applicable to the CubeSat in such a way as to equip themselves with a system that speed up the return and, at the same time, guarantee it safety in the same re-entry phase. Furthermore, the group of the invention and structured to be applicable, whenever cenesialanece ss it ä , all those C ube S atchene are dimensionally compatible. STATE OF THE ART TL CubeSat is a type of miniaturized satellite developed since 1999 by the State University 25 California Polytechnic University and Stanford University. CubeSats are made up of many units of different sizes standards and their overall size may increase adding units of the same size even along a only axis. The development of CubeSats has allowed a notable reducing costs in the satellite world by revolutionizing, thus, access to space and opening new frontiers for universities, research institutions and emerging companies. Today CubeSats are used for a wide range of 10 of space missions, from terrestrial observations to satellite communications and scientific research. As the CubeSat market expands, 51 is felt there is an ever-increasing need for solutions capable of guaranteeing greater flexibility and safety in missions 15 spatial. In particular, the 1st is particularly felt requires that 1 CubeSat be equipped with an effective system and reliable for their return at the end of the mission or in case of emergency. In fact, during the return phase the vehicles lose their kinetic energy by converting it into heat through friction with the gases in the atmosphere surrounding the vehicle itself. Heat is transferred to the gases in the atmosphere around the vehicle and the fluid tends to aerodynamic heating by convection, conduction and radiation through 10 25 layer of viscous geese surrounds the vehicle giving life to the so-called “aerodynamic heating”. In this regard, the vase is lined as a “heat shield” has long been considered an essential part of a vehicle spacecraft that must make an atmospheric reentry or that is moves at high speed in a planet's atmosphere. Its the purpose is precisely to protect the vehicle from heat which 51 develops when it moves at high speed in a atmosphere. As may be obvious to a technician in the field, a 10 this problem is particularly felt when the The vehicle also hosts a payload for space experiments. Another need relating to the CubeSat sector that of being able to ensure and speed up their return (de-orbiting) at the end of the mission. 15 In fact, it is now known to technicians in the sector that the number of satellites circling the Earth in orbits between 500 and 1000 km (LEO - Low Earth Orbit) is in constant growth and, to avoid orbital saturation, begins to there is a strong need to create solutions 20 that facilitate the re-entry of the satellites once finished the mission. In particular, while at low altitudes (<450 km) atmospheric drag naturally deorbits the spacecraft, at higher altitudes (>450 km) the drag 25 is less meaningful and technologies need to be developed of deorbiting. Current developments make use of sails deployable but are too complex and bulky for the small satellites (up to 200 kg) . Obviously , equipped with the device - orbiting, as well as of a thermal shield, entails, nece ss airly , additionally important expenditure in both economic and engineering terms. How much above would be at odds with philosophy of the C ube S atche , as indicated above , disclosed diffusion to its characteristics of cost-effectiveness and companion tt and zz a Er here indi felt the need to dispose of a solution that would allow CubeSats to be equipped with a de-orbiting and thermal protection device without per 15 this burden on the costs and size of CubeSats same. The inventors of the present invention have created a single group capable of equipping the CubeSats both of a de-orbiting device and of a protection thermal. The group of the present invention is physically independent from the CubeSat but is structured in such a way as to be able to be applied on the CubeStat itself if there is one need. DESCRIPTION OF THE INVENTION 25 The object of the present invention is a group of de- orbiting and thermal protection to be applied to CubeSats and characterized by the fact that it includes an AL frame fastening, capable of being reversibly fixed to a external perimeter of① a load-bearing structure of a relative CubeSat, and a plurality of arms fixed to the said frame fixing by means of a plurality of respective hinges and suitable for supporting a heat shield; said group comprising a 1position indicator fixed to the CubeSat and capable of cooperate with a contrasting portion of said frame and reversible fastening means for fixing said frame 10 fixing to the CubeSat. Preferably, this position indicator is fixed to the said supporting structure of the CubeSat. Preferably, said position indicator is a spherical spring pin. 15 Preferably, said contrast portion is a cavity capable of being reversibly engaged by the said spherical pin. Preferably, said reversible fastening means They are composed of a screw and nut complex. 20 Preferably, said fixing frame has a border square interior and a polygonal outer border with a number of sides greater than or equal to six. Preferably, said hinges are fixed to said polygonal external edge and said fixing means 25 reversible engage said square inner edge. BRIEF DESCRIPTION OF THE SIGNS For a better understanding of this invention An embodiment for this purpose is described below. comprehensive and non-limiting with the aid of figures to all egate, incui: - Figure 1 is a perspective view of a group of de-orbiting and thermal protection according to this invention applied to a related CubeSat; - figure 2 illustrates a detail of figure 1 with 10 parts removed for clarity; - figure 3 illustrates a second detail of the figure 1 with parts removed for clarity; and - figure 4 illustrates a third detail of the figure 1 with parts removed for clarity. 15 FORMA DIA TTU PREFERRED ACTION OF THE INVENTION Figure 1, is indicated as a whole with 1 a de-orbiting and thermal protection group according to the present invention. The de-orbiting and thermal protection group 1 comprises a fixing frame 2 and a plurality of arms 3 fixed to the fixing frame 2 by means of a respective plurality of hinges 4. The fixing frame 2 has an internal edge 5 square in shape and an outer edge 6 octagonal in shape. 25 Inner board 5 ¢ , unused , arranged against a bearing structure 7 of a CubeSat 8 to which it is fixed reversibly as will be described below. Hinges are fixed to the outer octagonal edge 4 that , then , sonofi ssa teadunafirst 3 a of the 3 arms. The presence of hinges 4 ensures that at the stage of orbital positioning , space launch , branches are arranged parallel to each other for the purpose of keep the heat shield in its folded conformation 10 and, only subsequently, 1 arms 51 open the rage causing 1the opening of the thermal shield. Specifically, the heat shield, known and not represented in the fig ures for simplicity, has a substantially similar conformation truncated cone-shaped surface with a smaller edge fixed in 15 matching fixing frame 2, and a border larger fixed to locking pins 9 arranged in a second end 3b of the arms 3. The opening of the arms 3 will be controlled by one of the known devices and not described here for simplicity and also because its nature is not a relevant aspect of the present invention as a whole. The de-orbiting and thermal protection group 1 comprises a spherical type spring pin 10 (figure 2) which It has the function of a position indicator. As illustrated 25 in figure 3, the spherical type spring pin 10 cooperates with a groove 11 obtained in the internal edge 5 and which has 1a contrast portion function for 1 indication of the correct relative positioning between the fixing frame 2 and the supporting structure 7 of the CubeSat 8. In use, the frame of fixing 2 is arranged to surround a portion of end of the supporting structure 7 of the CubeSat 8, on which is slid until the ball-type spring pin 1 0 does not engage the groove ⑪ . In this case point you are certain that the correct position has been reached 10 positioning of the fixing frame relative to the load-bearing structure 7. As illustrated in figure 4, the reversible fastening of the fixing frame 2 to the supporting structure 7 It occurs through a nut 12 / bolt 13 coupling. 15 In this regard, it should be emphasized that, in itself, in the load-bearing structures 7 is still obtained a plurality of through holes that can be used for the housing of both the spherical type spring pin 10 and of bolt 13. 20 The assembly of the present invention provides a device that ensures thermal protection during CubeSat reentry like heat shields of the known art applied to satellites of size major. 25 At the same time, the group of the present invention develops a passive deorbit device for CubeSats, which exploits the interaction with the Earth's atmosphere, the magnetosphere or ionosphere to accelerate decay of the CubeSat in the atmosphere. This will help ensure, for example, the future CubeSats for telecommunications comply with the requirements ESA Clean Space, and therefore that LEO satellites will limit the their presence in the protected region (up to 2000 km) at 5 years from the end of the mission or 5 years from the date of 10 injection, if they do not have the ability to maneuver recurrently. In particular, relatively high-orbiting, it was assessed that the application of the group according to this invention on a CubeSat reduces its de- orbiting (from 600 km to 400 km) from five years to just one year. 15 From the above it is clear that the group of the present invention represents a solution whose technical features ensure both de-orbiting and the thermal protection of the CubeSats without, for this, harm neither the economy nor the compactness of CubeSat themselves. In summary, the de-orbiting and shielding cluster thermal of the present invention represents an important evolutionary process of C ube S at , or providing a solution complete and highly reliable for space missions 25 request safe entry and check G raziea ll a Its innovative design and compatibility with the existing structures, this group positions itself as a ideal choice for future CubeSat missions, contributing aga rant the success and safety of oni operations spaces.

Claims

1. De-orbiting and thermal protection assembly (1) to be applied to CubeSats and characterised by the fact that it comprises a fixing frame (2), suitable for being reversibly fixed to an external perimeter of a load-bearing structure (7) of a relative CubeSat (8), and a plurality of arms (3) fixed to said fixing frame (2) by means of a plurality of respective hinges (4) and suitable for supporting a heat shield; said assembly comprising a position indicator (10) fixed to the CubeSat (8) and suitable for cooperating with a contrast portion (11) of said fixing frame (2) and reversible fixing means (10, 11) for fixing said fixing frame (2) to the CubeSat (8).

2. De-orbiting and thermal protection group according to claim 1, characterised in that said position indicator (10) is fixed to said supporting structure (7) of the CubeSat (8).

3. De-orbiting and thermal protection group according to claim 2, characterised in that said position indicator is a spherical type spring pin (10).

4. De-orbiting and thermal protection group according to claim 3, characterised in that said contrast portion is a cavity (11) suitable to be reversibly engaged by said spherical pin (10).

5. De-orbiting and thermal protection group according to one of the preceding claims, characterised in that said reversible fixing means are composed of a screw (13) and nut (12) assembly.

6. De-orbiting and thermal protection assembly according to one of the preceding claims, characterised in that said fixing frame (2) has a square internal edge (5) and a polygonal external edge (6) with a number of sides greater than or equal to six.

7. De-orbiting and thermal protection assembly according to claim 6, characterised in that said hinges (4) are fixed to said external edge (6) and said reversible fixing means (10, 11) engage said internal edge (5).