WO2012166046A2 - Mélanges de monoergol liquide à base de dinitramide d'ammonium utilisables et stockables à basse température - Google Patents

Mélanges de monoergol liquide à base de dinitramide d'ammonium utilisables et stockables à basse température Download PDF

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Publication number
WO2012166046A2
WO2012166046A2 PCT/SE2012/050589 SE2012050589W WO2012166046A2 WO 2012166046 A2 WO2012166046 A2 WO 2012166046A2 SE 2012050589 W SE2012050589 W SE 2012050589W WO 2012166046 A2 WO2012166046 A2 WO 2012166046A2
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Prior art keywords
weight
adn
monopropellant
ammonia
water
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PCT/SE2012/050589
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English (en)
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WO2012166046A3 (fr
Inventor
Peter THORMÄHLEN
Kjell Anflo
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Ecaps Ab
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Publication date
Application filed by Ecaps Ab filed Critical Ecaps Ab
Publication of WO2012166046A2 publication Critical patent/WO2012166046A2/fr
Publication of WO2012166046A3 publication Critical patent/WO2012166046A3/fr

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
    • C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
    • C06D5/08—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more liquids
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B31/00—Compositions containing an inorganic nitrogen-oxygen salt

Definitions

  • the present invention relates to ammonium dinitramide (ADN) based liquid mon- opropellant blends exhibiting improved storability and operational range in terms of having a reduced lower operational temperature limit.
  • ADN ammonium dinitramide
  • the inventive monopro- pellant belongs to a type of monopropellants generally being referred to as High Performance Green Propulsion (HPGP) monopropellants.
  • HPGP High Performance Green Propulsion
  • the monopropellants are especially suited for rocket propulsion, other vessel or vehicle propulsion, and gas generation. More particularly the present invention relates to such propellants especially suited for space, and deep space applications, and suitable for storage, and operation in close proximity to cryogenic propulsion systems, and
  • WO 2002/096832 discloses stable, liquid monopropellants based on ammonium dinitramide, having improved combustion characteristics.
  • the propellants are low-hazardous both from a handling point of view and from an environmental point of view, and exhibit a low toxicity, low flammability, a high theoretical specific impulse, high density. Moreover such propellants are easily ignitable by means of a controlled ignition mechanism, and at the same time exhibit a low sensitivity.
  • hydrazine which solidifies at 1°C
  • such propellants must be storable and operational at temperatures within the range of 10°C and 50°C.
  • the most preferred propellants of WO 2002/096832 are composed of ADN, water, glycerol, and a stabilizer, or ADN water, methanol, and a stabilizer.
  • a composition consisting of about 64.3% ammonium dinitramide, about 24.3 % water and about 11.4% by weight of methanol, (this composition is also being designated as LMP- 103) to which composition a stabiliser is added in an amount of 0.1 to 5 %, more typically 0.5-3 and preferably 0.5- 1 by weight based upon the other components.
  • the above monopropellant is an example of a newly developed type of monopropellants referred to as High Performance Green Propulsion (HPGP) monopropellants.
  • HPGP High Performance Green Propulsion
  • the monopropellants of WO 2002/096832 can for example be used for the pur- pose of orbit manoeuvring and attitude control of satellites, and other space vehicles, in which case rocket engines, or thrusters are often used in short bursts or pulses, the duration of which typically can be fractions of seconds to several hours.
  • rocket engines, or thrusters are commonly used with a nominal thrust of typically 0.5 N to 3 kN.
  • the monopropellant designated LMP- 103S which is composed of 63.0% by weight of ADN, 18.4% by weight of methanol, 4.6% by weight of ammonia, the balance to 100% being water, and which is an example of the monopropellants disclosed in WO 2002/096832, tends to undergo saturation with respect to the dissolved ADN, which forms solid crystals in the mixture of liquid solvents when the temperature of the monopropellant is being lowered to about -7°C.
  • propellant for the above-mentioned purposes, which propellant should exhibit the above-mentioned desired characteristics of the above-mentioned liquid ADN-based HPGP monopropellant, and which propellant should remain a homogenous solution at temperatures below -7°C.
  • the propellant should remain homogeneous at temperatures down to -15°C. More preferably, the propellant should remain homogeneous at temperatures down to -30°C.
  • the present inventors have surprisingly found that the low-temperature storabil- ity and operational range of a HPGP monopropellant comprising ADN, water, and ammonia, such as LMP- 103S, could be substantially improved.
  • monopropellants having a composition comprising:
  • monopropellant blends within the above specified range have been found to be a homogenous solution down to -30°C. It is believed that according to the invention monopropellants can even be obtained which remain homogeneous solutions down to temperatures of -40°C.
  • An improved low-temperature operational range of the monopropellant will have the advantage of less energy being required for heating the monopropellant during storage and operation. Accordingly, an energy providing system having reduced capacity, complexity and weight can therefore be used. This will also reduce the associated costs. As will be understood, each degree C of reduced tem- perature that the monopropellant will be tolerable to will be of substantial importance.
  • any crystallization occurring in the inventive monopropellants during cooling thereof has been found to be reversible, that is, the crystals formed will dis- solve again upon heating of the monopropellant.
  • the required heating has been found to generally correspond to an increase of 5- 10°C from the point of the observed saturation temperature.
  • the inventive mono- propellant blends will also allow for being stored and used in a closer proximity to cryogenic tanks than the prior art ADN-based liquid HPGP monopropellants, while at the same time requiring reduced extent heating during storage.
  • the inventive monopropellant blends will generally not require heating from the above-mentioned low temperatures up to a propellant feed temperature of e.g. 20°C before they are injected and ignited in the thruster. Instead, the monopropellants, as long as they are still homogenous, can be used directly, already at a low temperature. That is, the inventive monopropellants are operational at low temperatures.
  • the term "monopropellant”, as used in the present disclosure, may more correctly be referred to as “monopropellant blend”, since the inventive propellant comprises more than one chemical compound.
  • the terms “monopropellant” and “monopropellant blend”, however, have been used interchangea- bly to denote the inventive propellant.
  • ammonia refers to pure NH3. Consequently, if aqueous ammonia is being used in preparing the inventive monopropellants, when establishing the water content of the monopropellant being prepared, the water contained in the ammonia must be taken into account.
  • the improved low-temperature operational range will also make the inventive monopropellants suitable for land/ sea/ air-based systems stored and used in cold conditions, such as e.g. artic conditions, in for example gas generators, APUs, underwater vehicles, etc.
  • the reduced low-temperature operational limit of the ADN-based monopropellant has been found to be governed by the temperature at which saturation with respect to ADN will occur, or, the temperature at which solidification of the monopropellant blend will occur, whichever is the higher temperature of the two.
  • the inventive monopropellant will not be affected by moderate presence of particulate matter in the monopropellants.
  • monopropellants having a composition comprising:
  • liquid monopropellant of the invention comprises: 55-62 % by weight of ammonium dinitramide;
  • the balance water Such monopropellant blend will remain a homogenous solution down to a temperature of -15°C, or below. More preferably, the liquid monopropellant of the invention comprises:
  • the water content of the inventive monopropellant based upon the above ranges of ADN, ammonia and methanol, as specified in respect of the above three different embodiments, will typically range from 4 % to 41 %, preferably from 7 % to 36 %, and more preferably from 10 % to 31 % by weight.
  • ammonia may conveniently be used as a 25% aqueous solution when preparing the inventive monopropellants. This will produce a ratio of ammonia to water of 1 :3 in the resulting monopropellant, unless additional water, or additional pure ammonia is being added. Accordingly, in one embodiment of the inventive monopropellant the ratio of ammonia to water is about 1:3. Additional water may for example be added in cases where a lower combustion temperature is desired.
  • stepwise testing was performed, wherein the monopropellant blend was kept at 0°C during one week, then at -5°C for one week, - 10°C for one week, - 15°C for one week, -20°C for one week, -25°C for one week, and, finally at -30°C for one week.
  • the objective of the present invention is to provide monopropellant blends having improved low-temperature operational and storability properties. Due to the reduced content of the highly energetic oxidizer compound ADN in the claimed monopropellants, the claimed monopropellant blends may in some instances exhibit a somewhat reduced, while still fully sufficient, performance, as compared to the preferred methanol-containing monopropellant of WO 2002/096832 referred to above.
  • a monopropellant blend was prepared consisting of
  • a monopropellant blend was prepared consisting of
  • Crystallisation (of ADN) occurred at -20°C.
  • the crystals dissolved again upon heating to about -10°C.
  • a monopropellant blend was prepared consisting of
  • the monopropellant blend of Example 3 is storable down to at least -30°C.
  • the performance of the monopropellant blend was verified on a 22 N thruster.
  • the monopropellant readily ignited with a propellant feed temperature of about 20°C, and the combustion was stable.
  • the specific impulse (I sp ) of the monopropellant on the 22 N thruster was found to be essentially the same as that of hydrazine when used on a corresponding thruster of similar thrust designed for operation on hydrazine.
  • the density of the monopropellant blend was found to be 20% higher than that of hydrazine.
  • a monopropellant blend was prepared consisting of
  • the monopropellant blend of Example 4 having a higher ADN content than the blends of Examples 1-3, is storable down to at least -30°C.

Abstract

L'invention concerne des monoergols liquides à base de dinitramide d'ammonium contenant de l'ADN, de l'eau, de l'ammoniaque et, éventuellement du méthanol, présentant une gamme d'utilisations à basse température améliorée.
PCT/SE2012/050589 2011-06-01 2012-06-01 Mélanges de monoergol liquide à base de dinitramide d'ammonium utilisables et stockables à basse température WO2012166046A2 (fr)

Applications Claiming Priority (8)

Application Number Priority Date Filing Date Title
US201161492187P 2011-06-01 2011-06-01
SE1100431-4 2011-06-01
US61/492,187 2011-06-01
SE1100431 2011-06-01
US201161535545P 2011-09-16 2011-09-16
SE1150847-0 2011-09-16
US61/535,545 2011-09-16
SE1150847 2011-09-16

Publications (2)

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WO2012166046A2 true WO2012166046A2 (fr) 2012-12-06
WO2012166046A3 WO2012166046A3 (fr) 2013-01-24

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013169193A1 (fr) 2012-05-09 2013-11-14 Ecaps Ab Réacteur amélioré pour monopropergols liquides à base de dinitramide d'ammonium, et propulseur comprenant ce réacteur
WO2013169192A1 (fr) 2012-05-09 2013-11-14 Ecaps Ab Réacteur amélioré pour monopropergols liquides à base de dinitramide d'ammonium, et propulseur comprenant ce réacteur
WO2014189450A1 (fr) 2013-05-20 2014-11-27 Ecaps Ab Monoergols liquides riches en comburant destinés à un moteur-fusée à propulsion chimique bimode
WO2014193300A1 (fr) 2013-05-29 2014-12-04 Ecaps Ab Moteur-fusée chimique bimode, et système de propulsion bimode comprenant le moteur-fusée
JP2016069228A (ja) * 2014-09-30 2016-05-09 カーリットホールディングス株式会社 液体推進薬及びその製造方法
EP3018112A1 (fr) 2014-11-06 2016-05-11 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Combustible de generateur de gaz a base de dinitramide d'ammonium (adn) et son procede de fabrication
EP3324028A1 (fr) 2016-11-17 2018-05-23 ECAPS Aktiebolag Moteur de fusée pour mélanges de propulsion liquide stockable à basse température et procédé de démarrage d'un tel moteur
CN109206284A (zh) * 2018-09-27 2019-01-15 西南科技大学 基于荷叶效应制备超疏水氧化剂的方法
WO2022043327A1 (fr) 2020-08-26 2022-03-03 LabOrbital GmbH Dispositif de production de gaz très chaud avec un carburant monergol ionique et allumage basse tension

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002096832A1 (fr) 2001-05-28 2002-12-05 Svenska Rymdaktiebolaget Monergols liquides a base de dinitramide d'ammonium presentant une stabilite de combustion et une duree de stockage ameliorees

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EP0950648A1 (fr) * 1998-04-15 1999-10-20 Nederlandse Organisatie Voor Toegepast-Natuurwetenschappelijk Onderzoek Tno Système propulsif à base de monoergol liquide
US6254705B1 (en) * 1999-02-26 2001-07-03 Svenska Rymdaktiebolaget Liquid propellant
US6984273B1 (en) * 1999-07-29 2006-01-10 Aerojet-General Corporation Premixed liquid monopropellant solutions and mixtures
WO2002095207A1 (fr) * 2001-05-23 2002-11-28 Svenska Rymdaktiebolaget Reacteur de decomposition de monergols liquides a base de dinitramide d'ammonium et procede de decomposition correspondant

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002096832A1 (fr) 2001-05-28 2002-12-05 Svenska Rymdaktiebolaget Monergols liquides a base de dinitramide d'ammonium presentant une stabilite de combustion et une duree de stockage ameliorees

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013169192A1 (fr) 2012-05-09 2013-11-14 Ecaps Ab Réacteur amélioré pour monopropergols liquides à base de dinitramide d'ammonium, et propulseur comprenant ce réacteur
JP2015517620A (ja) * 2012-05-09 2015-06-22 イーシーエイピーエス・アクチボラグ アンモニウムジニトラミドベースの液体単元推進薬のための改善されたリアクタ、および、そのようなリアクタを含むスラスタ
WO2013169193A1 (fr) 2012-05-09 2013-11-14 Ecaps Ab Réacteur amélioré pour monopropergols liquides à base de dinitramide d'ammonium, et propulseur comprenant ce réacteur
US10316794B2 (en) 2013-05-20 2019-06-11 Ecaps Ab Dual mode chemical rocket engine and dual mode propulsion system comprising the rocket engine
WO2014189450A1 (fr) 2013-05-20 2014-11-27 Ecaps Ab Monoergols liquides riches en comburant destinés à un moteur-fusée à propulsion chimique bimode
WO2014189451A1 (fr) 2013-05-20 2014-11-27 Ecaps Ab Moteur-fusée à propulsion chimique bimode et système de propulsion bimode comportant le moteur-fusée
WO2014193300A1 (fr) 2013-05-29 2014-12-04 Ecaps Ab Moteur-fusée chimique bimode, et système de propulsion bimode comprenant le moteur-fusée
JP2016069228A (ja) * 2014-09-30 2016-05-09 カーリットホールディングス株式会社 液体推進薬及びその製造方法
DE102014016299A1 (de) 2014-11-06 2016-05-12 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR) Gasgenerator-Treibstoff auf der Basis von Ammoniumdinitramid (ADN) und Verfahren zu seiner Herstellung
EP3018112A1 (fr) 2014-11-06 2016-05-11 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Combustible de generateur de gaz a base de dinitramide d'ammonium (adn) et son procede de fabrication
EP3324028A1 (fr) 2016-11-17 2018-05-23 ECAPS Aktiebolag Moteur de fusée pour mélanges de propulsion liquide stockable à basse température et procédé de démarrage d'un tel moteur
CN109206284A (zh) * 2018-09-27 2019-01-15 西南科技大学 基于荷叶效应制备超疏水氧化剂的方法
CN109206284B (zh) * 2018-09-27 2021-03-09 西南科技大学 基于荷叶效应制备超疏水氧化剂的方法
WO2022043327A1 (fr) 2020-08-26 2022-03-03 LabOrbital GmbH Dispositif de production de gaz très chaud avec un carburant monergol ionique et allumage basse tension
DE102020122337A1 (de) 2020-08-26 2022-03-03 LabOrbital GmbH Heißgaserzeugungsvorrichtung mit monergolem ionischen Treibstoff und Niederspannungsanzündung

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