GB2525941A - Propulsion for aerospace applications - Google Patents

Propulsion for aerospace applications Download PDF

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Publication number
GB2525941A
GB2525941A GB1410571.2A GB201410571A GB2525941A GB 2525941 A GB2525941 A GB 2525941A GB 201410571 A GB201410571 A GB 201410571A GB 2525941 A GB2525941 A GB 2525941A
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GB
United Kingdom
Prior art keywords
frozen gas
solid
gas
heating fluid
propulsion
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.)
Withdrawn
Application number
GB1410571.2A
Other versions
GB201410571D0 (en
Inventor
Stephen Desmond Lewis
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB201410571D0 publication Critical patent/GB201410571D0/en
Publication of GB2525941A publication Critical patent/GB2525941A/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/26—Burning control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

Propulsion for a rocket engine is provided by a frozen gas in solid or liquid form 1 that is heated by a heating fluid or a working fluid 2 in the combustion chamber of a rocket 3 to provide thrust. The frozen gas may be carbon dioxide in solid form or nitrogen or hydrogen in liquid form. The heating or working fluid may be water. A cylinder of frozen gas may be fed using springs 4 which provide pressure against a grill (5, figure 2), such that when the heating fluid is injected against the frozen gas 6 it will be turned into gas and consumed and continuously fed by the pressure from the springs. The heating fluid is pumped into the combustion chamber by a pump 7.

Description

Propulsion for aerospace applications This invention relates to a method of propulsion that is designed to be as safe as possible for civilian use, particularly as a final mode of propulsion for reaching orbit.
Currently the only practical way of anyone reaching space, even with assistance from air-breathing engines, is with the use of rockets. Some have been shown to be safer than others however they all leave a lot to be desired, the most dangerous part being the use of oxidisers. Steam powered rockets avoid the use of oxidiser however their tanks need to be heavy to accommodate the pressure, negating their advantages. To overcome this, the present invention proposes a frozen gas in solid and/or liquid form, said frozen gas in solid and/or liquid form heated by a heating fluid and/or working fluid in the combustion chamber of a rocket engine to produce thrust.
The frozen gas will be inert and benign until it is heated in the combustion chamber of the rocket by the heating fluid, when it quickly turns to gas and expands. Because the frozen gas will not require to be heated by a substantial amount the working fluid can be stored at a lower temperature and therefore pressure than a steam rocket propellant tank enabling lighter tanks for the frozen gas and the heating fluid.
Preferably, said frozen gas is carbon dioxide in solid form and/or liquid nitrogen and/or liquid hydrogen.
Preferably, said heating fluid is water.
An example of the invention will now be described by referring to the accompanying drawing: -figure 1 shows a side view of the propulsion for aerospace applications and; -figure 2 shows an end view of the propulsion for aerospace applications according to the invention.
A frozen gas in solid and/or liquid form 1 which may be carbon dioxide in solid form or liquid nitrogen or liquid hydrogen is heated by a heating and/or working fluid 2, which may be water, in the combustion chamber of a rocket 3. Figure 1 shows an arrangement in which a cylinder of frozen carbon dioxide is fed using springs 4 which provide pressure against a grill 5, shown in figure 2, such that when the heating fluid is injected against the frozen gas 6 it will be turned into gas and consumed and cntinuously fed by the pressure from the springs. The heating fluid is pumped into the combustion chamber by a pump 7. If liquid nitrogen or liquid hydrogen is used the process would employ conventional liquid fuelled rocket technology.
The very low temperatures and no use of oxidiser and general inertness of the components may provide a very safe alternative to traditional rocket engines.
Due to the low working temperature of the rocket the rocket engine can be made to be very lightweight and can potentially be very reliable. This may also result in a lower cost engine.
There may be possibilities of utilising waste heat from air-breathing engines to provide extra heat to the heating fluid.
The heating fluid can be heated before the launch of a rocket or an aircraft/spacecraft and could be insulated, or frictional heating from atmospheric flight could prime the fluid ready for the rocket cycle.
The frozen gas can be stored in such a way that it is vented and can also be insulated.
Spare liquid hydrogen left over from an air-breathing engine flight could then be utilised with the heating fluid without needing a separate fuel tank, or higher density propellants could be chosen instead such as liquid nitrogen or solid carbon dioxide.

Claims (3)

  1. Claims 1 A frozen gas in solid and/or liquid form, said frozen gas in solid and/or liquid form heated by a heating fluid and/or working fluid in the combustion chamber of a rocket engine to produce thrust.
  2. 2 A frozen gas in solid and/or liquid form according to claim 1, wherein said frozen gas is carbon dioxide in solid form and/or liquid nitrogen and/or liquid hydrogen.
  3. 3 A frozen gas in solid and/or liquid form according to any of the preceding claims, wherein said heating fluid is water.
GB1410571.2A 2014-05-10 2014-06-13 Propulsion for aerospace applications Withdrawn GB2525941A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB1408418.0A GB201408418D0 (en) 2014-05-10 2014-05-10 Propulsion for aerospace applications

Publications (2)

Publication Number Publication Date
GB201410571D0 GB201410571D0 (en) 2014-07-30
GB2525941A true GB2525941A (en) 2015-11-11

Family

ID=51032652

Family Applications (2)

Application Number Title Priority Date Filing Date
GBGB1408418.0A Ceased GB201408418D0 (en) 2014-05-10 2014-05-10 Propulsion for aerospace applications
GB1410571.2A Withdrawn GB2525941A (en) 2014-05-10 2014-06-13 Propulsion for aerospace applications

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GBGB1408418.0A Ceased GB201408418D0 (en) 2014-05-10 2014-05-10 Propulsion for aerospace applications

Country Status (1)

Country Link
GB (2) GB201408418D0 (en)

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
halfbakery, "liquid nitrogen brine rocket" [online] 22 May 2011. Available from: http://www.halfbakery.com/idea/liquid_20nitrogen_20brine_20rocket [Accessed 19 November 2014] *

Also Published As

Publication number Publication date
GB201408418D0 (en) 2014-06-25
GB201410571D0 (en) 2014-07-30

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)