CN115435644A - Shell case of shell accelerating airship and airship - Google Patents
Shell case of shell accelerating airship and airship Download PDFInfo
- Publication number
- CN115435644A CN115435644A CN202110605847.2A CN202110605847A CN115435644A CN 115435644 A CN115435644 A CN 115435644A CN 202110605847 A CN202110605847 A CN 202110605847A CN 115435644 A CN115435644 A CN 115435644A
- Authority
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- China
- Prior art keywords
- airship
- shell
- cannonball
- fuel
- cartridge case
- 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
- 239000000446 fuel Substances 0.000 claims abstract description 34
- 238000002485 combustion reaction Methods 0.000 claims abstract description 19
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical group [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 14
- 239000001301 oxygen Substances 0.000 claims description 14
- 229910052760 oxygen Inorganic materials 0.000 claims description 14
- 238000004804 winding Methods 0.000 claims description 11
- 239000000835 fiber Substances 0.000 claims description 9
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 8
- 239000004917 carbon fiber Substances 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 8
- 239000002657 fibrous material Substances 0.000 claims description 6
- 239000007800 oxidant agent Substances 0.000 claims description 6
- 230000001590 oxidative effect Effects 0.000 claims description 5
- 239000007921 spray Substances 0.000 claims description 5
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052749 magnesium Inorganic materials 0.000 claims description 4
- 239000011777 magnesium Substances 0.000 claims description 4
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- -1 polypropylene Polymers 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 239000004743 Polypropylene Substances 0.000 claims 1
- 239000003638 chemical reducing agent Substances 0.000 claims 1
- 239000000203 mixture Substances 0.000 claims 1
- 229920001155 polypropylene Polymers 0.000 claims 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 19
- 239000002360 explosive Substances 0.000 description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 4
- 229910052802 copper Inorganic materials 0.000 description 4
- 239000010949 copper Substances 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 238000004364 calculation method Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 239000004698 Polyethylene Substances 0.000 description 2
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 229920000573 polyethylene Polymers 0.000 description 2
- 241000967522 Eruca pinnatifida Species 0.000 description 1
- OTMSDBZUPAUEDD-UHFFFAOYSA-N Ethane Chemical compound CC OTMSDBZUPAUEDD-UHFFFAOYSA-N 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 229910000861 Mg alloy Inorganic materials 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 229910001385 heavy metal Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- FUJCRWPEOMXPAD-UHFFFAOYSA-N lithium oxide Chemical compound [Li+].[Li+].[O-2] FUJCRWPEOMXPAD-UHFFFAOYSA-N 0.000 description 1
- 229910001947 lithium oxide Inorganic materials 0.000 description 1
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 description 1
- 239000000395 magnesium oxide Substances 0.000 description 1
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000004570 mortar (masonry) Substances 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000002760 rocket fuel Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/72—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material
- F42B12/76—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the material of the casing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/409—Unconventional spacecraft propulsion systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41B—WEAPONS FOR PROJECTING MISSILES WITHOUT USE OF EXPLOSIVE OR COMBUSTIBLE PROPELLANT CHARGE; WEAPONS NOT OTHERWISE PROVIDED FOR
- F41B6/00—Electromagnetic launchers ; Plasma-actuated launchers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electromagnetism (AREA)
- Plasma & Fusion (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Abstract
The present invention relates to a shell of shell accelerating airship and its airship. After receiving the cannonball, the airship utilizes fuel and a rocket engine to generate thrust so as to accelerate the airship. The charge ratio of the common cannonball is very low. The present invention provides a projectile with high charge ratio, and a combustion furnace matched with the airship, and the shell left after the projectile takes out fuel can be combusted in the combustion furnace. The combination can greatly improve the charging ratio by times, the equivalent specific impulse of the cannonball can be improved by more than 5 times, the utilization rate of the cannonball is greatly increased, the using amount of the cannonball is greatly reduced, and the requirement of the electromagnetic cannon system on scale is saved.
Description
Technical Field
The invention relates to the technology of space, rocket engine, chemical fuel, electromagnetic cannon, etc., in particular to the design of a cannonball accelerating airship system.
Background
Patent 2020108535240 discloses a projectile acceleration system and an acceleration method thereof, which mainly comprises the following steps: the electromagnetic cannon sequentially launches a series of cannonballs, and the cannonballs contain jet fuel; the shells fly towards the airship, and the airship receives the shells in sequence; the airship takes out the fuel in the shells after receiving one shell, puts the fuel into a rocket engine and jets air backwards, thereby accelerating the airship. After the fuel of the cannonball is taken out, the cannonball is discarded in the space, and becomes space garbage.
The cannonball needs a shell to store fuel, the current common shell is made of steel and copper, the density of heavy metals reaches 7.8-9kg/L, and the ratio of the fuel mass of the cannonball to the total weight of the cannonball is too small. Even the charge is typically only 15-20% higher than the highest high explosive, mortar projectiles. The reason is that the impact of the shell is large when the shell is launched, the strength of the shell can be ensured only by adopting a thick shell, the density of the shell is large, and the density of the explosive is small, so that the charge ratio of the shell is very small. In particular, the density of the fuel of the rocket engine used as the explosive charge of the electromagnetic cannonball in space is smaller than that of the explosive, so that the explosive charge ratio is smaller when the common cannonball is adopted.
The fuel is filled in the common cannonball, the specific impulse of the common rocket fuel can reach 3500-4200m/s, and if the cannonball in 1kg is filled with 0.15kg of fuel, the equivalent specific impulse of the cannonball can be calculated as follows: 0.15 × 3500/1=525m/s,0.15 × 4200/1=630m/s, that is, the equivalent specific impulse of a normal shell is 525 to 630m/s.
Disclosure of Invention
The present invention provides a shell with high effective charge ratio, its shell is made of combustible material, and on the airship a combustion furnace is mounted, and in the combustion furnace an oxidant is introduced, and the shell can be placed in the furnace to burn. The projectiles carry fuel, which is divided into oxidant and oxidizer. By combustible cartridge casing is meant a cartridge casing capable of combustion in an oxidant. A large amount of high-temperature and high-pressure gas generated by burning the cartridge case by the combustion furnace can be introduced into the turbine to generate electricity. High temperature and high pressure gas can also be used to heat the heat, thereby increasing the specific impulse of the fuel.
Further, the specific impulse of the combustible cartridge casing can often reach 2500-3500m/s. The outlet of the combustion furnace is provided with a spray pipe, the combustion pressure is kept above 1MPa, the combustion furnace and the spray pipe form a rocket engine at the time, and the jet speed can reach 2500-3500m/s, so that the accelerating effect of the cannonball is greatly improved. The impulse generated by the shell jet is converted into the impulse of fuel, and the equivalent charge ratio of the cannonball can be calculated. The equivalent charge ratio is much higher than that of the common cannonball.
Advantageous effects
Through the combination, the utilization rate of the cartridge case can be greatly improved, and the equivalent specific impulse of the shell is improved.
The density of combustible material is 1.5-2.7kg/L, which is far lower than steel and copper, thus greatly reducing the weight of the cartridge case and increasing the charge ratio from 5-10% to more than 80%.
The cartridge case made of the fiber material has 3-8 times higher specific strength than steel and copper, so that the use amount of the cartridge case can be much less than that of the steel and the copper according to volume calculation, thereby further reducing the quality of the cartridge case and improving the charge ratio.
If the combustible material is made of fiber materials, the fiber materials have high combustion speed and can generate a large amount of high-temperature and high-pressure gas, and the fiber materials can be used as a rocket engine to generate thrust after being added with the jet pipe. Thereby enhancing the accelerating effect of the cannonball.
The combustible material, whether made of fiber material or aluminum, magnesium, lithium and the like, can be combusted in oxygen, and the generated heat can preheat the fuel, so that the specific impulse of the fuel is improved by more than 10 percent. The power generation can also be carried out by a thermoelectric generator.
If the combustible material is made of aluminum, magnesium and lithium, the combustible material is burnt to generate aluminum oxide, magnesium oxide and lithium oxide, which are all high-temperature resistant materials and can be used for generating the fairing of the airship. Fairings may be used to protect against heat during the deceleration landing of the airship in the atmosphere after reaching the target planet.
By the measures, the equivalent specific impulse of the cannonball is improved by more than 6-7 times, and the using amount of the cannonball can be reduced by more than 60-85%.
The construction scale and the manufacturing cost of the electromagnetic gun system are greatly reduced.
Examples
Example 1 (1, 2, 3, 4)
A shell accelerating system for accelerating an airship in space is deployed on the second Lagrangian point of the earth. The acceleration system consists of an electromagnetic gun and a cannonball, and the system runs in the outer space; the cannonball is placed in an electromagnetic cannon to be launched, and the electromagnetic cannon is powered by a power supply. The cannonball is filled with fuel which is solid oxygen and solid methane, and the specific impulse of the fuel is 3800m/s. The launching speed of the electromagnetic cannon is adjustable so as to launch cannonballs with different speeds. The airship is equipped with a rocket engine, a catching device, which can catch projectiles flying nearby. The airship is provided with a rocket engine, and the fuel of the cannonball can be used for igniting and jetting the air by the rocket engine to generate thrust so as to drive the airship to accelerate.
The shell of the cannonball is made of carbon fiber, the carbon content of the carbon fiber is 90%, and the balance is mainly hydrogen. The thickness of the cartridge case is 0.1cm, the length is 20cm and the diameter is 10cm. The circumference and the bottom of the shell are provided with a shell, the front end of the shell is not provided with the shell, the surface area of the shell is 726cm ^2, the volume is 0.073L, the density of carbon fiber is 2.5kg/L, and the weight of the shell is 0.18kg. The volume of the cannonball is 1.57L, the average density of the fuel is 0.9kg/L, and 1.41kg of fuel can be filled. The total weight of the cannonball is 0.18+1.41=1.59kg, and the charge ratio reaches 88.6 percent.
The cannonball is communicated with the communication equipment of the electromagnetic cannon and the communication equipment on the airship in the flying process, and the flying direction of the cannonball is continuously adjusted. The capturing device is a net, the airship is provided with a net, the length and the width of the net are respectively 5 meters, and the net is vertical to the flying direction. When the cannonball meets the flying boat, the speed difference between the cannonball and the flying boat is less than 5m/s so as to avoid damaging the net by collision. Each projectile catches up with the airship and is captured by the airship. The velocity of the projectile is substantially constant during flight.
And the airship is provided with a combustion furnace and a spray pipe, as well as a cutter. After the fuel of the shell is taken out, the cutter is opened to cut the shell, the shell is put into a combustion furnace, and oxygen is introduced to burn the shell.
The pressure of the combustion furnace is kept at 3MPa, and high-temperature and high-pressure fuel gas generated by combustion is introduced into the spray pipe to generate a specific impulse of 3300 m/s. 0.48kg of oxygen is needed to burn 0.18kg of carbon fiber, and the sum of the two is 0.18+0.48=0.66kg. And the ratio of methane to oxygen for reaction with methane is 1.41-0.48=0.93kg. The equivalent specific impulse calculation method of the cannonball comprises the following steps: (0.93 + 3800+0.66 + 3300)/1.59 =3592m/s, which is 6-7 times higher than the equivalent specific impulse of the common cannonball.
Example 2 (5, 8)
The other is the same as the previous embodiment except that:
the cylindrical circumference of the cartridge case is formed by spirally winding a carbon fiber film, the winding direction of the carbon fiber film is spirally wound, and the winding angle (helix angle) is 20 degrees. The winding angle of the spiral makes the front and the back of the cartridge case closer.
The fuel is solid ethane and solid oxygen, the average density is 1kg/L, and the fuel with high density can be filled with more fuel.
In addition, the shell case is burnt in the combustion furnace, so that the shell case is prevented from becoming space garbage, and the pollution to the space is reduced.
Example 3 (6, 9, 10)
The rest is the same as example 1 except that:
the circumference of the cartridge case is formed by winding polyethylene fiber films, the winding angle of the fibers is 0 degree, and the number of winding layers is 4. The thinner the fiber, the more the number of layers wound, the more uniform the cartridge case and the stronger the adhesive force.
The front end of the shell is towards the front of the launching direction, and the rear end is close to the rear of the launching direction. When the gun is launched, the front end is slightly extruded, and the rear end is greatly extruded. The fiber film is of unequal thickness, with a small thickness at the front end and a large thickness at the rear end. Therefore, the wall thickness of the front end of the wound cartridge case is small and is only 0.1mm, and the wall thickness of the rear end reaches 1mm. The density of the polyethylene fiber is only 0.98kg/L, the weight of the cartridge case is only 0.05kg, the charge is 1.41kg, the total weight is 0.05+1.41=1.46kg, and the charge ratio is up to 1.41/1.46=96.6%.
0.13kg of oxygen is required to burn 0.05kg of carbon fiber, and the sum of the two is 0.05+0.13=0.18kg. And the sum of methane, oxygen for reaction with methane, is 1.41-0.13=1.28kg. The equivalent specific impulse calculation method of the cannonball comprises the following steps: (1.28 + 3800+0.18 + 3300)/1.46 =3738m/s, which is 6-7 times higher than the equivalent specific impulse of the common shell. This value is already very close to 3800m/s, which corresponds almost to the entire mass of the projectile being fuel.
Example 4 (7)
The rest is the same as example 1, except that:
the cartridge case is made of aluminum magnesium alloy, and the mass of aluminum and magnesium accounts for 90% of the total mass of the cartridge case. Part of oxygen of the rocket engine is introduced into the combustion furnace, and the oxygen is excessive, so that the aluminum magnesium is combusted to generate a large amount of heat, and the excessive oxygen is heated to 1500 ℃. Excess oxygen is introduced into the rocket engine again, and the oxygen reacts with methane to generate a specific impulse of 4500m/s, so that the specific impulse of the fuel is greatly improved. The shell of the cannonball accounts for 30 percent of the total weight of the cannonball, the generated equivalent specific impulse is (1-0.3) × 4500/1=3150m/s, and the equivalent specific impulse of the cannonball is more than 5 times of that of the common cannonball filled with fuel.
Claims (10)
1. An acceleration system consists of an electromagnetic cannon and an airship, wherein the electromagnetic cannon launches cannonballs, the cannon contains fuel, and the fuel comprises an oxidant and a reducing agent; the airship can receive the shells, take out the fuel in the shells and put into the rocket engine to generate thrust, so that the airship is accelerated; the method is characterized in that:
the shell of the cannonball is made of combustible materials, and the shell is combustible in an oxidant;
the airship is provided with a combustion furnace, and the cartridge case can be burnt in the combustion furnace.
2. The system of claim 1, wherein: the cartridge case is made of a fibrous material.
3. The system of claim 2, wherein: the winding direction of the fibers on the circumference of the cartridge case is spirally wound, and the winding angle is greater than or equal to 0 degree and less than or equal to 30 degrees.
4. The system of claim 2, wherein: the winding angle of the fibers on the circumference of the cartridge case is 0 degree, and the number of winding layers is more than or equal to 3.
5. The system of claim 2, wherein: the carbon content of the cartridge case is greater than 70%.
6. The system of claim 2, wherein: the fibers are carbon fibers or polypropylene fibers.
7. The system of claim 1, wherein: in the composition of the cartridge case, the mass of aluminum, magnesium and lithium accounts for the total ratio, and is more than 70%.
8. The system of claim 1, wherein: the cartridge case has a small wall thickness at the front end and a large wall thickness at the rear end.
9. The system of claim 1, wherein: the fuel is a two-component fuel in which one component is oxygen.
10. The system of claim 1, wherein: and a spray pipe is arranged at the outlet of the combustion furnace.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110605847.2A CN115435644A (en) | 2021-06-01 | 2021-06-01 | Shell case of shell accelerating airship and airship |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110605847.2A CN115435644A (en) | 2021-06-01 | 2021-06-01 | Shell case of shell accelerating airship and airship |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115435644A true CN115435644A (en) | 2022-12-06 |
Family
ID=84239967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110605847.2A Pending CN115435644A (en) | 2021-06-01 | 2021-06-01 | Shell case of shell accelerating airship and airship |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115435644A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4318344A (en) * | 1979-12-03 | 1982-03-09 | The United States Of America As Represented By The Secretary Of The Navy | Spinning tubular projectile combustible sabot |
| US5237928A (en) * | 1988-07-28 | 1993-08-24 | Dynamit Nobel Aktiengesellschaft | Combustible cartridge case |
| US5544587A (en) * | 1993-12-13 | 1996-08-13 | Rheinmetall Industrie Gmbh | Cannon ammunition having combustible cartridge case |
| US20090266263A1 (en) * | 2008-04-25 | 2009-10-29 | Alliant Techsystems Inc. | Advanced muzzle loader ammunition |
| CN105737671A (en) * | 2014-12-10 | 2016-07-06 | 华东师范大学附属枫泾中学 | Space weapon |
| CN111928730A (en) * | 2020-08-26 | 2020-11-13 | 珠海达理宇航科技有限公司 | Electromagnetic shell accelerating system and accelerating method thereof |
-
2021
- 2021-06-01 CN CN202110605847.2A patent/CN115435644A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4318344A (en) * | 1979-12-03 | 1982-03-09 | The United States Of America As Represented By The Secretary Of The Navy | Spinning tubular projectile combustible sabot |
| US5237928A (en) * | 1988-07-28 | 1993-08-24 | Dynamit Nobel Aktiengesellschaft | Combustible cartridge case |
| US5544587A (en) * | 1993-12-13 | 1996-08-13 | Rheinmetall Industrie Gmbh | Cannon ammunition having combustible cartridge case |
| US20090266263A1 (en) * | 2008-04-25 | 2009-10-29 | Alliant Techsystems Inc. | Advanced muzzle loader ammunition |
| CN105737671A (en) * | 2014-12-10 | 2016-07-06 | 华东师范大学附属枫泾中学 | Space weapon |
| CN111928730A (en) * | 2020-08-26 | 2020-11-13 | 珠海达理宇航科技有限公司 | Electromagnetic shell accelerating system and accelerating method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 金泽渊等: "火***与装药概论", 兵器工业出版社, pages: 188 * |
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Application publication date: 20221206 |