EP0022391B1 - Dispositif cryostatique destiné à supporter des accélérations - Google Patents

Dispositif cryostatique destiné à supporter des accélérations Download PDF

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Publication number
EP0022391B1
EP0022391B1 EP19800400905 EP80400905A EP0022391B1 EP 0022391 B1 EP0022391 B1 EP 0022391B1 EP 19800400905 EP19800400905 EP 19800400905 EP 80400905 A EP80400905 A EP 80400905A EP 0022391 B1 EP0022391 B1 EP 0022391B1
Authority
EP
European Patent Office
Prior art keywords
tank
orifice
primary
cryostatic
cryostatic device
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP19800400905
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0022391A1 (fr
Inventor
Christian Henri Hamon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Societe Anonyme de Telecommunications SAT
Original Assignee
Societe Anonyme de Telecommunications SAT
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Anonyme de Telecommunications SAT filed Critical Societe Anonyme de Telecommunications SAT
Publication of EP0022391A1 publication Critical patent/EP0022391A1/fr
Application granted granted Critical
Publication of EP0022391B1 publication Critical patent/EP0022391B1/fr
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C3/00—Vessels not under pressure
    • F17C3/02—Vessels not under pressure with provision for thermal insulation
    • F17C3/08—Vessels not under pressure with provision for thermal insulation by vacuum spaces, e.g. Dewar flask
    • F17C3/085—Cryostats
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C3/00—Vessels not under pressure
    • F17C3/02—Vessels not under pressure with provision for thermal insulation
    • F17C3/08—Vessels not under pressure with provision for thermal insulation by vacuum spaces, e.g. Dewar flask
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2203/00—Vessel construction, in particular walls or details thereof
    • F17C2203/03—Thermal insulations
    • F17C2203/0391—Thermal insulations by vacuum
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2203/00—Vessel construction, in particular walls or details thereof
    • F17C2203/06—Materials for walls or layers thereof; Properties or structures of walls or their materials
    • F17C2203/0602—Wall structures; Special features thereof
    • F17C2203/0612—Wall structures
    • F17C2203/0626—Multiple walls
    • F17C2203/0629—Two walls
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
    • F17C2205/01—Mounting arrangements
    • F17C2205/0123—Mounting arrangements characterised by number of vessels
    • F17C2205/013—Two or more vessels
    • F17C2205/0149—Vessel mounted inside another one
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C2270/00—Applications
    • F17C2270/05—Applications for industrial use
    • F17C2270/0509—"Dewar" vessels
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S220/00—Receptacles
    • Y10S220/901—Liquified gas content, cryogenic
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/8593—Systems
    • Y10T137/86187—Plural tanks or compartments connected for serial flow
    • Y10T137/86228—With communicating opening in common walls of tanks or compartments

Definitions

  • This patent relates to a cryostatic device intended to be taken on board a vehicle capable of undergoing significant accelerations in several directions.
  • Such devices essentially consist of a reservoir which is filled with a cryogenic liquid, liquid air, liquid nitrogen or other, prior to the departure of the vehicle, such as an unmanned aircraft or drone; said tank, after having undergone the accelerations due to the departure and to the modifications of the trajectory of said vehicle, must still contain enough cryogenic liquid to allow it to be operational during the scheduled time.
  • cryostatic devices are in the form of a double-walled tank with a filling orifice at the top. It is easily understood that this simple cryostatic device placed, such as a bottle, in a vehicle empties through its upper orifice if the vehicle is subjected to a significant vertical acceleration, said to be positive because of the same direction as gravity. An acceleration greater than that of gravity is considered important.
  • the cryostatic device according to the invention which is a cryostatic device comprising an internal wall and an external wall joined in their upper parts by the filling orifice, the vacuum being created between the two walls, is remarkable in that the cryogenic liquid reservoir, which is delimited by the internal wall, is divided by a separating partition into two reservoirs, a primary reservoir and a secondary reservoir, in that the secondary reservoir surrounds all or part of the primary reservoir, in that that the filling orifice terminates in the secondary tank and in that the primary tank and the secondary tank communicate through an orifice situated in the separating partition at a level such that the volume of the primary reservoir located below said orifice is approximately equal at the volume located above this same orifice in this same tank.
  • said communication orifice is then located approximately halfway up said primary reservoir.
  • the cryostatic device will advantageously include one or more capillary conduits in the upper part of the separating partition. Said capillary conduits are located approximately above the communication orifice, for example in the case of a cylindrical primary reservoir on the same generator or on neighboring generators.
  • the cryostatic device according to the invention will have a poorer behavior only for accelerations in the same direction as the movement of the drone but in the opposite direction to this movement; in practice, this type of acceleration is rarely encountered.
  • the communication orifice between the primary tank and the secondary tank will advantageously be protected by a deflector located inside said primary tank.
  • the main advantage of the cryostatic device according to the invention lies in the fact that the cryogenic liquid is kept as much as possible in said cryostatic device despite the accelerations to which it is likely to be subjected in different directions.
  • Tests carried out on a cryostatic device according to the invention, on board a drone, have shown that a quantity of cryogenic liquid equivalent to half of the capacity of the primary reservoir was preserved whatever the number, the intensity and the direction of said accelerations, it being understood that the accelerations in the same direction as the movement of the drone and in the opposite direction are statistically few during a flight.
  • Another advantage of the cryostatic device according to the invention lies in the fact that the secondary tank, which partially or completely surrounds the primary tank, has an additional role of cooling the walls of the primary tank, which reduces the evaporation of the cryogenic liquid at contact of these.
  • FIGS 1 and 2 show two embodiments of the cryostatic device according to the invention.
  • FIGS 3 and 4 each show a sectional view of a cryostatic device according to the invention provided with various improvements.
  • Figure 5 is a section orthogonal to the previous of a cryostatic device provided with an improvement by facilitating the emptying.
  • FIG. 1 the external wall of the cryostatic device according to the invention is shown in 1 and, in 2, the internal wall of this same device. Between these two walls 1 and 2, according to the usual and known technique, the vacuum was made in 3.
  • a separating partition 4 divides the reservoir of cryogenic liquid delimited by the internal wall 2, into two reservoirs, the reservoir primary 5 and secondary tank 6.
  • An orifice 7 pierced in the partition 4 approximately halfway up the primary reservoir 5 communicates said primary reservoir 5 with the secondary reservoir 6 itself extended by the filling orifice 8.
  • FIG. 1 The device shown by way of example in FIG. 1 is of cylindrical shape and FIG. 1 represents a section along two diametrically opposite generatrices of this device. No relation is imposed between the height and the diameter of said cryostatic device.
  • said cryostatic device When said cryostatic device is on board a drone, it is placed in a vertical position, the filling orifice 8 being at its upper part, and the communication orifice 7 being placed towards the front of the drone, the direction normal movement of said drone being represented by the arrow 9.
  • the communication orifice 7 must remain small relative to the height of the primary reservoir 5, this communication orifice 7 is of circular or oval section.
  • the diameter of the filling orifice 8 has here been limited to reduce losses by conduction. Its exact position can be chosen according to the characteristics of the accelerations undergone in use and possibly the resistance of the materials used.
  • cryostatic device may include all the arrangements necessary for its use and well known elsewhere.
  • various elements 10 to be cooled and in the external wall 1 can be included a zone 11 transparent to certain radiations and an element 12 vacuum-tight and carrying electrical passages 13.
  • the walls 1 and 2 and the partition 4 can be made of glassware, but it is obvious that a metallic embodiment, for example copper alloy or stainless steel, does not depart from the scope of the present invention. In the case of an embodiment in glassware, it will be useful, according to the known technique, to metallize the walls to reduce the heat losses by radiation.
  • FIG. 2 is also a sectional view of a cryostatic device according to the invention.
  • said cryostatic device represented in this FIG. 2, for reasons of convenience of technological implementation, the internal wall 2 has a recess 15 at the base of which the partition 4 is fixed.
  • the same elements different embodiments of the device according to the invention are identified by the same numbers.
  • FIG. 3 highlights some improvements of the cryostatic device according to the invention. Depending on the case, said improvements can be used independently of each other or simultaneously.
  • the first of said improvements consists of one or more capillary conduits 16 connecting the primary reservoir 5 to the secondary reservoir 6, said capillary holes 16 being located in the upper part of the separating partition 4.
  • the purpose of said capillary holes 16 is to facilitate filling of the primary tank 5, in particular they allow almost complete filling of the primary tank 5, while in their absence, the filling level is limited to the right of the communication orifice 7.
  • a second improvement of the cryostatic device according to the invention resides in the fixing of a deflector 17 near the communication orifice 7.
  • This deflector is located inside the primary tank 5 and below the communication orifice 7.
  • the presence of the deflector 17 greatly reduces the quantity of cryogenic liquid ejected by the orifice 7.
  • a second deflector 18 can also be placed also inside the primary tank 5, but above the communication orifice 7.
  • a third improvement of the cryostatic device according to the invention consists of an extension 19, inside the secondary tank 6, of the filling orifice 8.
  • the purpose of this extension 19 is to retain as much as possible the cryogenic liquid which is in the secondary tank 6, inside the cr y o-static device according to the invention.
  • FIG. 5 is a section along A-A of the cryostatic device shown in FIG. 4, this FIG. 5 explains the shape of the slopes 20 and 21.
  • FIG. 4 highlights another possible improvement of the cryostatic device according to the invention.
  • This improvement lies in the fact that the upper part of the separating partition 4 has a slight concavity 22 oriented so that it forms a bowl under the filling orifice 8, so that, from the start of filling, a a certain quantity of cryogenic liquid collects in said bowl and improves the conditions for cooling the cryostatic device according to the invention.
  • cryostatic devices described above and represented by the drawings, are given only by way of example.
  • the use of cylindrical volumes is not imperative and, depending on various requirements, one can very well use'volumes of sections square, rectangular, oval or other.
  • the main use of the cryostatic device according to the invention is obviously the conservation of cryogenic liquid on board vehicles subjected to strong accelerations.
  • cryostatic device can also be adapted to transport any liquid on board a vehicle subjected to strong accelerations.
  • the outer wall 1 of said device can be omitted.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
EP19800400905 1979-06-29 1980-06-19 Dispositif cryostatique destiné à supporter des accélérations Expired EP0022391B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7916840 1979-06-29
FR7916840A FR2460441A1 (fr) 1979-06-29 1979-06-29 Dispositif cryostatique pouvant supporter des accelerations

Publications (2)

Publication Number Publication Date
EP0022391A1 EP0022391A1 (fr) 1981-01-14
EP0022391B1 true EP0022391B1 (fr) 1982-08-11

Family

ID=9227276

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19800400905 Expired EP0022391B1 (fr) 1979-06-29 1980-06-19 Dispositif cryostatique destiné à supporter des accélérations

Country Status (6)

Country Link
US (1) US4337624A (enExample)
EP (1) EP0022391B1 (enExample)
JP (1) JPS5828479B2 (enExample)
CA (1) CA1127066A (enExample)
DE (1) DE3060756D1 (enExample)
FR (1) FR2460441A1 (enExample)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59106000A (ja) * 1982-12-08 1984-06-19 Mizota Kogyo Kk ポンプ据付装置
US4925060A (en) * 1989-08-17 1990-05-15 Gustafson Keith W Cork for cryogenic dry shipper
US5633583A (en) * 1995-06-07 1997-05-27 Gas Research Institute Magnetic telescope with enhanced noise suppression
DE10352575B3 (de) * 2003-11-11 2005-05-04 Leica Microsystems Nussloch Gmbh Kryostat mit einem Innenbehälter zur Aufnahme eines Mikrotoms
US8651313B1 (en) * 2009-09-01 2014-02-18 The Boeing Company Underwater cryogenic storage vessel
US8859153B1 (en) 2009-09-01 2014-10-14 The Boeing Company Thermal conditioning fluids for an underwater cryogenic storage vessel
WO2018065658A1 (en) * 2016-10-05 2018-04-12 Wärtsilä Finland Oy A fuel tank unit

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US662217A (en) * 1899-03-29 1900-11-20 John F Brady Means for conserving liquid gases.
US1535642A (en) * 1922-01-30 1925-04-28 John G Armknecht Fuel-reserve tank
US1561102A (en) * 1924-04-30 1925-11-10 Purox Company Vacuum container
FR734613A (fr) * 1931-04-08 1932-10-24 Air Liquide Procédé et dispositif de vidange et de remplissage de récipients d'emmagasinement pour gaz liquéfiés
US2293263A (en) * 1941-01-14 1942-08-18 Linde Air Prod Co Method of and apparatus for storing liquefied gas mixtures
US2389168A (en) * 1944-07-03 1945-11-20 Mahlon C Snyder Means for storing liquid fuel
US2643022A (en) * 1947-08-15 1953-06-23 Union Carbide & Carbon Corp Radiation shield supports in vacuum insulated containers
US2719583A (en) * 1951-01-02 1955-10-04 Phillips Petroleum Co Fuel tank for aircraft
US2845199A (en) * 1955-01-06 1958-07-29 Mine Safety Appliances Co Container
FR1237018A (fr) * 1958-10-06 1960-11-23 Union Carbide Corp Récipient à double paroi pour gaz liquéfiés
US3144756A (en) * 1962-07-23 1964-08-18 Ion Physics Corp Vacuum system cooling trap
FR1605141A (enExample) * 1968-07-02 1973-03-16
SU634069A1 (ru) * 1974-04-04 1978-11-25 Куйбышевский Ордена Трудового Красного Знамени Авиационный Институт Им. С.П.Королева Переохладитель сжиженного газа
US3984222A (en) * 1974-12-23 1976-10-05 Cryogenic Technology, Inc. Dewar cooling device
CH658890A5 (de) * 1983-03-04 1986-12-15 Schweizerische Lokomotiv Antriebseinrichtung mit variabler gesamtuebersetzung.

Also Published As

Publication number Publication date
JPS566995A (en) 1981-01-24
FR2460441B1 (enExample) 1982-01-29
FR2460441A1 (fr) 1981-01-23
EP0022391A1 (fr) 1981-01-14
CA1127066A (en) 1982-07-06
US4337624A (en) 1982-07-06
JPS5828479B2 (ja) 1983-06-16
DE3060756D1 (en) 1982-10-07

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