CN103834445A - Fuel - Google Patents
Fuel Download PDFInfo
- Publication number
- CN103834445A CN103834445A CN201310643762.9A CN201310643762A CN103834445A CN 103834445 A CN103834445 A CN 103834445A CN 201310643762 A CN201310643762 A CN 201310643762A CN 103834445 A CN103834445 A CN 103834445A
- Authority
- CN
- China
- Prior art keywords
- fuel
- rocket
- ether
- aluminum hydride
- density
- 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.)
- Pending
Links
Landscapes
- Liquid Carbonaceous Fuels (AREA)
Abstract
The invention provides fuel. The fuel comprises 26-35wt% of aluminum trihydride and 65-74wt% of ethyl ether. Aluminum trihydride is high-energy fuel, can be dissolved in ethyl ether and can greatly improve fuel density to more than 1.5g/cm<3> so that a rocket volume is reduced effectively and emission payload is improved and thus the fuel is suitable for emission of 150-1500t of a rocket and can be used for space station construction and civil space motion.
Description
Technical field
The present invention relates to a kind of fuel, especially rocket fuel.
Background technology
Rocket engine is the one of jet engine, and the reactant in propellant tank or launch vehicle (propelling agent) is become to high-speed jet, because newton's second law of motion produces thrust.Rocket engine can be used for spacecraft propulsion, also can be used for guided missile etc. and flies in endoatmosphere.
Current most of rocket engine is all to adopt liquid fuel, and the specific impulse of solid is little, but the density of liquid fuel is smaller at present, picture kerosene etc., density is at 0.84 gram/cc, and density is little like this can increase kerosene hold-up vessel volume, thus entire effect rocket load.
Summary of the invention
The invention provides a kind of highdensity rocket fuel.
Technical scheme is as follows:
A kind of fuel, is characterized in that being made up of ether and three aluminum hydride, and wherein three aluminum hydride content are 26~35wt%, and ether is 65~74% wt%.
Because three aluminum hydride are also high energy fuels, can dissolve in ether like this, more than can increasing considerably the density to 1.5 gram/cc of fuel, thereby reduce rocket volume, improve transmitting workload.
Embodiment
In concrete enforcement, there are multiple implementation details and prioritization scheme:
1. while making, three aluminum hydride are dissolved in ether, mixture is kept to-10 degrees Celsius of following low temperature.
2. in fuel, suitably add aluminium powder.
The rocket launching that is suitable for 150~1500 tons of the present invention, builds and civilian space activity for space station.
Claims (3)
1. a fuel, is characterized in that being made up of ether and three aluminum hydride, and wherein three aluminum hydride content are 26~35wt%, and ether is 65~74% wt%.
2. a kind of fuel according to claim 1, is dissolved in three aluminum hydride in ether while it is characterized in that making, and mixture is kept to-10 degrees Celsius of following low temperature.
3. a kind of fuel according to claim 1, is characterized in that suitably adding aluminium powder in fuel.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201310643762.9A CN103834445A (en) | 2013-12-05 | 2013-12-05 | Fuel |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201310643762.9A CN103834445A (en) | 2013-12-05 | 2013-12-05 | Fuel |
Publications (1)
Publication Number | Publication Date |
---|---|
CN103834445A true CN103834445A (en) | 2014-06-04 |
Family
ID=50798346
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201310643762.9A Pending CN103834445A (en) | 2013-12-05 | 2013-12-05 | Fuel |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN103834445A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109694759A (en) * | 2019-03-07 | 2019-04-30 | 西安近代化学研究所 | A kind of punching engine slurry fuel |
-
2013
- 2013-12-05 CN CN201310643762.9A patent/CN103834445A/en active Pending
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109694759A (en) * | 2019-03-07 | 2019-04-30 | 西安近代化学研究所 | A kind of punching engine slurry fuel |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
Waltrup et al. | History of US Navy ramjet, scramjet, and mixed-cycle propulsion development | |
US9139311B2 (en) | Reusable global launcher | |
Calabro | Overview on hybrid propulsion | |
CN108688829A (en) | Solid-liquid power sub-orbital booster | |
US20220372932A9 (en) | Ramjet propulsion method | |
Fry et al. | The US Navy's Contributions to Airbreathing Missile Propulsion Technology | |
US9970740B2 (en) | Viscous liquid monopropellant | |
CN103834445A (en) | Fuel | |
US20140007758A1 (en) | Pollution-free liquid balancing device | |
RU2532321C2 (en) | Light-class single-stage carrier rocket | |
Townend | Domain of the Scramjet | |
Waltrup et al. | History of US Navy ramjet, scramjet, and mixed-cycle propulsion development | |
Kile et al. | VI. Indian nuclear forces | |
CN106833762A (en) | A kind of low freezing point fuel and preparation method thereof | |
Kim et al. | Supercavitating Rocket System | |
RU2492123C1 (en) | Carrier rocket first stage fly-back booster built around unified rocket unit | |
Wingborg | High performance solid ADN propellant for space applications | |
Kemburi | High-speed cruise missiles in Asia: evolution or revolution in fire power? | |
Cleaver | Rockets and assisted take-off | |
Predoi et al. | Comparative analysis regarding hybrid rocket engines with single or multi-stages | |
Ismail | Oxygen/aluminium metal powder space propulsion system: a literature review & trade-off analysis | |
Postol | North Korean Long-Range Ballistic Missiles and US Missile Defenses | |
TYAGI | New Acquisitions by People’s Liberation Army and Pakistan’s Armed Forces | |
Nagappa et al. | Pakistan's Babur-3 Submarine Launch Cruise Missile (SLCM): An Assessment (R59-2017) | |
RU2518499C1 (en) | Single-stage booster |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140604 |