CN112179215B - Flight guidance weapon control device based on plasma jet technology - Google Patents
Flight guidance weapon control device based on plasma jet technology Download PDFInfo
- Publication number
- CN112179215B CN112179215B CN202010996239.4A CN202010996239A CN112179215B CN 112179215 B CN112179215 B CN 112179215B CN 202010996239 A CN202010996239 A CN 202010996239A CN 112179215 B CN112179215 B CN 112179215B
- Authority
- CN
- China
- Prior art keywords
- plasma jet
- plasma
- shell
- excitation
- flight guidance
- 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.)
- Active
Links
- 238000005516 engineering process Methods 0.000 title claims abstract description 17
- 230000005284 excitation Effects 0.000 claims abstract description 47
- 238000002347 injection Methods 0.000 claims abstract description 20
- 239000007924 injection Substances 0.000 claims abstract description 20
- 239000003990 capacitor Substances 0.000 claims description 10
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 2
- 239000000463 material Substances 0.000 claims 1
- 238000000926 separation method Methods 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 238000007750 plasma spraying Methods 0.000 description 6
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
- F42B10/668—Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/107—Simultaneous control of position or course in three dimensions specially adapted for missiles
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a flight guided munition control device based on plasma jet technology, which comprises four plasma jet shells arranged at the head of a flight guided munition shell, wherein the axis of each plasma jet shell is vertical to the surface of the flight guided munition shell, a plasma jet orifice is arranged on the surface of each plasma jet shell, an opening corresponding to the plasma jet orifice is also arranged on the corresponding cavity of the head of the flight guided munition, and the plasma jet orifices are superposed with the openings; each plasma injection shell inner wall is also provided with a plasma excitation electrode unit, and the plasma injection shell further comprises an injection control system and a high-voltage direct-current power supply which are arranged in the flight guidance weapon and are mutually connected, and each plasma excitation electrode unit is connected with the injection control system. The device can reduce the aerodynamic drag of flight, has improved weapon's flying speed and flying distance.
Description
Technical Field
The invention belongs to the technical field of guided weapon control, and particularly relates to a flight guided weapon control device based on a plasma jet technology.
Background
At present, the existing active flight guidance weapon mostly adopts the front and back longitudinal row missile wing layout, wherein the front missile wing is responsible for maneuvering steering, and the tail wing is responsible for stabilizing flight attitude. However, in high-speed flight of the weapon, the aerodynamic resistance of the front missile wing can be obviously increased along with the increase of the flight speed, and particularly, in the case of high-angle-of-attack maneuvering flight, the flight resistance generated by the front missile wing accounts for nearly 70% of the total aerodynamic resistance, so that the energy reserve of the weapon is greatly consumed, and the maneuvering performance and the operational efficiency of the weapon are restricted. If the front missile wing can be cancelled on the premise of ensuring the requirement of weapon control precision, the key technical and tactical indexes such as flight speed, maximum attack distance and the like of the flight guidance weapon can be greatly improved, and thus the killing efficiency of the weapon is further improved.
Disclosure of Invention
The invention aims to provide a flight guided weapon control device based on a plasma jet technology, which can replace the flight control function of a front missile wing of a flight guided weapon, reduce the aerodynamic drag of flight and improve the flying speed and flying distance of the weapon.
The technical scheme adopted by the invention is that the flight guidance weapon control device based on the plasma jet technology comprises four plasma jet shells arranged at the head part of a flight guidance weapon shell, wherein the head part of the flight guidance weapon is provided with four cavities for mounting the four plasma jet shells, the axis of each plasma jet shell is vertical to the surface of the flight guidance weapon shell, the surface of each plasma jet shell is provided with a plasma jet orifice, the corresponding cavity of the head part of the flight guidance weapon is also provided with an opening corresponding to the plasma jet orifice, and the plasma jet orifices are superposed with the openings; the four plasma jet shells are uniformly distributed on the same circumference of the head of the flight guidance weapon, a plasma excitation electrode unit is further arranged on the inner wall of each plasma jet shell, and the four plasma jet shells further comprise a jet control system and a high-voltage direct-current power supply which are arranged in the flight guidance weapon and are mutually connected, and each plasma excitation electrode unit is connected with the jet control system.
The present invention is also characterized in that,
the plasma jet shell is in a cylinder shape, the plasma excitation electrode unit and the plasma jet orifice are both arranged on the side wall of the cylinder, and the plasma excitation electrode unit and the plasma jet orifice are opposite to each other at an angle of 180 degrees; the plasma spray housing is an insulating housing.
The plasma jet shell is made of aluminum oxide.
The plasma excitation electrode unit comprises an excitation positive electrode and an excitation negative electrode, and the excitation positive electrode and the excitation negative electrode are respectively connected with the injection control system through binding posts.
The exposed length of the exciting positive electrode and the exciting negative electrode in the plasma jet shell is 1mm-5mm, and the spacing distance between the exciting positive electrode and the exciting negative electrode is 5mm-10mm.
The high-voltage DC power supply is a power supply for outputting 5-10 kV DC high-voltage signals.
The injection control system comprises a controller, a high-speed solid-state relay and a capacitor which are connected in sequence; the high-speed solid-state relay is also connected with a high-voltage direct-current power supply, and each excitation positive electrode and each excitation negative electrode are connected with the capacitor through the wiring terminal.
The controller is a singlechip with the chip model number of AT89S 51.
The model of the high-speed solid-state relay is ssr-100DD-H.
The capacitance of the capacitor is 0.05-0.5 microfarad, and the withstand voltage is not less than 5000V.
The invention has the beneficial effects that:
(1) The flight guidance weapon control device cancels the front missile wing of the flight guidance weapon, so that the pneumatic appearance of the weapon is smoother, the pneumatic resistance of flight is obviously reduced, and the flying speed and flying distance of the weapon are improved.
(2) The control device for the flight guided weapon adopts high-voltage pulse discharge, deflagration injection in the plasma injection shell, short-time rapid heating, strong instantaneous shock wave generation, strong control effect and low energy consumption.
(3) The invention relates to a flight guidance weapon control device, which forms instantaneous perturbation at the head of a weapon by the interaction of plasma jet and incoming flow, changes the topological structures of the streaming flow field and a vortex system of the weapon, amplifies the moment by a long force arm of the weapon, generates strong streaming pneumatic perturbation, further destroys the static stability state of the weapon, changes the course of the weapon, and achieves the purpose of controlling the flight guidance weapon by changing the course of the weapon.
Drawings
FIG. 1 is a schematic structural diagram of a flight guidance weapon control device based on plasma jet technology;
FIG. 2 is a structural schematic diagram of the flight guidance weapon control device based on the plasma jet technology, which is arranged on the head of a flight guidance weapon shell;
FIG. 3 is a top view of FIG. 2;
FIG. 4 is a schematic representation of the state of the air flow around the head of a flight guidance weapon when the control device of the present invention is not activated;
FIG. 5 is a schematic representation of the air flow conditions around the head of the flight guidance weapon after actuation of the control device of the present invention.
In the figure, 1, a plasma jet shell, 2, a jet control system, 3, a high-voltage direct-current power supply, 4, an excitation positive electrode, 5, an excitation negative electrode, 6, a binding post, 7, a plasma jet orifice, 8, a guide head, 9, a tail wing, 10, incoming current, 11, synthetic vortex and 12 control torque.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention relates to a flight guidance weapon control device based on a plasma jet technology, which comprises four plasma jet shells 1 arranged at the head part of a flight guidance weapon shell, wherein the head part of the flight guidance weapon is provided with four cavities for mounting the four plasma jet shells 1, the axis of each plasma jet shell 1 is vertical to the surface of the flight guidance weapon shell, the surface of each plasma jet shell 1 is provided with a plasma jet orifice 7, the corresponding cavity of the head part of the flight guidance weapon is also provided with an opening corresponding to the plasma jet orifice 7, and the plasma jet orifice 7 is superposed with the opening; the four plasma jet shells 1 are uniformly distributed on the same circumference of the head of the flight guidance weapon, the bottom of each plasma jet shell 1 is also provided with a plasma excitation electrode unit, and the plasma jet device further comprises a jet control system 2 and a high-voltage direct-current power supply 3 which are arranged in the flight guidance weapon and are mutually connected, and each plasma excitation electrode unit is connected with the jet control system 2.
The plasma jet casing 1 is in a cylinder shape, the plasma excitation electrode unit and the plasma jet orifice 7 are both arranged on the side wall of the cylinder, and the plasma excitation electrode unit and the plasma jet orifice 7 are opposite to each other at an angle of 180 degrees; the plasma spray housing 1 is an insulating housing.
The plasma spray housing 1 is made of alumina.
The plasma excitation electrode unit comprises an excitation positive electrode 4 and an excitation negative electrode 5, the electrodes are made of tungsten rods or copper rods, and the excitation positive electrode 4 and the excitation negative electrode 5 are respectively connected with the injection control system 2 through binding posts 6.
The exposed length of the exciting positive electrode 4 and the exciting negative electrode 5 in the plasma jet shell 1 is 1mm-5mm, and the spacing distance between the exciting positive electrode 4 and the exciting negative electrode 5 is 5mm-10mm.
The high-voltage direct-current power supply 3 is a power supply for outputting 5-10 kilovolt direct-current high-voltage signals.
The injection control system 2 comprises a controller, a high-speed solid-state relay and a capacitor which are connected in sequence; the high-speed solid-state relay is also connected with a high-voltage direct-current power supply 3, and each excitation positive electrode 4 and each excitation negative electrode 5 are connected with a capacitor through a binding post 6.
The controller is a singlechip of an Atmel company with the chip model number of AT89S 51.
The model of the high-speed solid-state relay is ssr-100DD-H.
The capacitance of the capacitor is 0.05-0.5 microfarad, and the withstand voltage is not less than 5000V.
As shown in fig. 2-3, the flight guidance weapon comprises a seeker 8 and a tail 9, the head of the flight guidance weapon is modified into four cavities with openings, the four cavities are uniformly distributed on the same circumference, the circle center falls on the central axis of the seeker 8, and the plasma jet shell 1 in the control device of the flight guidance weapon is arranged in the cavities.
The working principle of the flight guidance weapon control device based on the plasma jet technology is as follows: as shown in fig. 4, when no maneuvering flight signal is guided, the weapon is subjected to the aerodynamic force of the incoming flow 10 and is symmetrical left and right, and the weapon has no yawing moment; when receiving a flight control system control signal, the injection control system 2 activates the plasma excitation electrode unit in the corresponding injection plasma injection shell 1 according to the flight control system requirement, generates plasma discharge, rapidly heats the air in the plasma injection shell 1 within a few milliseconds, and the air rapidly expands, so that the gas pressure in the plasma injection shell 1 is rapidly increased, and the pressure/temperature is rapidly increased and is ejected from the only plasma injection port 7 of the plasma injection shell 1 at a high speed. As shown in fig. 5, the high-speed airflow interacts with the incoming flow 10, so that a synthetic vortex 11 is formed at the rear of the jet orifice along the airflow direction, the airflow near the wall surface is deflected, a control moment 12 is generated on one side of the jet cavity, the guided weapon is deflected, and the control purpose is achieved.
5-10 kV direct-current high-voltage signals output by the high-voltage direct-current power supply 3 enter from a power supply input port of the high-speed solid-state relay, and the controller adjusts the high-speed solid-state relay (the response time is less than 1 millisecond) in the injection control system to control the on-off of the power supply output signals according to control signals generated by operation. The power output signal charges the high voltage resistant capacitor (withstand voltage is larger than 5000V) of the corresponding control side, and when the voltage exceeds the plasma breakdown voltage between the positive excitation electrode and the negative excitation electrode, the plasma excitation electrode unit starts to discharge. During discharge, current reaches the positive excitation electrode and the negative excitation electrode through the binding posts, and then air between the positive electrode and the negative electrode is broken down in the plasma jet shell 1, so that plasma discharge is generated. The plasma discharge in the plasma spraying shell 1 rapidly heats the air in the plasma spraying shell 1, the temperature and the pressure in the plasma spraying shell 1 are sharply increased, high-temperature and high-pressure gas in the plasma spraying shell 1 is promoted to be sprayed out from the top plasma spraying port 7 at a high speed, and high-speed radial jet flow is formed outside the plasma spraying port 7.
The device can be widely applied to various flight guidance weapons such as air-to-air missiles, air-to-ground missiles, ground-to-air missiles, accurate guidance bombs and the like, and the traditional non-guidance weapons can also have guidance capability through simple modification.
The flight guidance weapon control device has the following advantages: firstly, the front missile wing of the guided weapon is cancelled, the aerodynamic resistance is greatly reduced, and the killing efficiency of the weapon is improved; secondly, engine gas of the weapon is not required to be used as a power source of a control surface; thirdly, no exposed part is arranged, the aerodynamic appearance of the surface of the weapon is not damaged, the air resistance is not increased, and extra flying interference torque is not generated; fourthly, the device has simple structure, flexibility and smallness, and is suitable for the modification of all flight guided weapons and non-guided weapons at present; and fifthly, no mechanical element exists, electric triggering is realized, the frequency response speed is high, the energy consumption is low, and the reliability is high. Sixthly, the system has light weight, low cost, relatively simple maintenance and long service life, greatly reduces the weight of the system compared with other solutions, and improves the reliability.
Claims (7)
1. A flight guidance weapon control device based on a plasma jet technology is characterized by comprising four plasma jet shells (1) arranged at the head of a flight guidance weapon shell, wherein the head of the flight guidance weapon is provided with four cavities for mounting the four plasma jet shells (1), the axis of each plasma jet shell (1) is perpendicular to the surface of the flight guidance weapon shell, the surface of each plasma jet shell (1) is provided with a plasma jet orifice (7), the corresponding cavity of the head of the flight guidance weapon is also provided with an opening corresponding to the plasma jet orifice (7), and the plasma jet orifices (7) are superposed with the openings; the four plasma jet shells (1) are uniformly distributed on the same circumference of the head of the flight guidance weapon, the inner wall of each plasma jet shell (1) is also provided with a plasma excitation electrode unit, and the four plasma jet shells further comprise a jet control system (2) and a high-voltage direct-current power supply (3) which are arranged in the flight guidance weapon and are mutually connected, and each plasma excitation electrode unit is connected with the jet control system (2);
the plasma jet shell (1) is in a cylinder shape, the plasma excitation electrode unit and the plasma jet orifice (7) are both arranged on the side wall of the cylinder, and the plasma excitation electrode unit and the plasma jet orifice (7) are opposite to each other at an angle of 180 degrees; the plasma jet shell (1) is an insulating shell;
the plasma excitation electrode unit comprises an excitation positive electrode (4) and an excitation negative electrode (5), and the excitation positive electrode (4) and the excitation negative electrode (5) are respectively connected with the injection control system (2) through binding posts (6);
the injection control system (2) comprises a controller, a high-speed solid-state relay and a capacitor which are connected in sequence; the high-speed solid-state relay is further connected with a high-voltage direct-current power supply (3), and each excitation positive electrode (4) and each excitation negative electrode (5) are connected with a capacitor through a binding post (6).
2. A plasma jet technology-based flight guidance weapon control device according to claim 1, characterized in that the material of the plasma jet housing (1) is alumina.
3. A plasma jet technology-based flight guidance weapon control device according to claim 1, characterized in that the exposed length of one excitation positive electrode (4) and one excitation negative electrode (5) in the plasma jet housing (1) is 1mm-5mm, and the separation distance between the excitation positive electrode (4) and the excitation negative electrode (5) is 5mm-10mm.
4. The control device for the flight guidance weapon based on the plasma jet technology as claimed in claim 1, wherein the high voltage direct current power supply (3) is a power supply outputting 5-10 kv direct current high voltage signal.
5. The plasma jet technology-based flight guidance weapon control device as claimed in claim 1, wherein the controller is a single chip microcomputer with a chip model number of AT89S 51.
6. The plasma jet technology-based flight guidance weapon control device of claim 1, wherein the high speed solid state relay is model number ssr-100DD-H.
7. The plasma jet technology-based flight guidance weapon control device of claim 1, wherein the capacitance of the capacitor is 0.05-0.5 microfarads, and the withstand voltage is not less than 5000 volts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010996239.4A CN112179215B (en) | 2020-09-21 | 2020-09-21 | Flight guidance weapon control device based on plasma jet technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010996239.4A CN112179215B (en) | 2020-09-21 | 2020-09-21 | Flight guidance weapon control device based on plasma jet technology |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112179215A CN112179215A (en) | 2021-01-05 |
| CN112179215B true CN112179215B (en) | 2023-03-21 |
Family
ID=73955657
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010996239.4A Active CN112179215B (en) | 2020-09-21 | 2020-09-21 | Flight guidance weapon control device based on plasma jet technology |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112179215B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937912B (en) * | 2021-01-21 | 2023-08-15 | 南京南华航空产业有限公司 | Rotary formation body lateral force control experimental device based on array type plasma |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108235553A (en) * | 2017-12-28 | 2018-06-29 | 西安理工大学 | Sliding discharge driver and its method for controlling plasma flow to slender bodies |
| CN108931160A (en) * | 2017-07-13 | 2018-12-04 | 王海龙 | A kind of turn emitter |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2912368B1 (en) * | 1998-07-08 | 1999-06-28 | 三菱電機株式会社 | Guided flying object and its guiding method |
| IL167721A (en) * | 2005-03-29 | 2008-06-05 | Israel Aerospace Ind Ltd | Steering system and method for guided flying apparatus |
| CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
| CN102943751B (en) * | 2012-11-27 | 2014-05-07 | 中国人民解放军国防科学技术大学 | Quick-response direct force generating device |
| CN103231796A (en) * | 2013-04-22 | 2013-08-07 | 哈尔滨工业大学 | Aircraft wing boundary layer separation inhibiting method based on plasma actuation |
| CN107037824B (en) * | 2017-06-09 | 2023-10-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Transverse control device and control method for flying wing model |
-
2020
- 2020-09-21 CN CN202010996239.4A patent/CN112179215B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108931160A (en) * | 2017-07-13 | 2018-12-04 | 王海龙 | A kind of turn emitter |
| CN108235553A (en) * | 2017-12-28 | 2018-06-29 | 西安理工大学 | Sliding discharge driver and its method for controlling plasma flow to slender bodies |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112179215A (en) | 2021-01-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7988103B2 (en) | Solid state supersonic flow actuator and method of use | |
| CN106184743A (en) | A kind of hypersonic aircraft fall by the use of thermal means controlled based on shock wave | |
| CN112179215B (en) | Flight guidance weapon control device based on plasma jet technology | |
| CA1216774A (en) | Process for the distribution of submunition | |
| US9752858B2 (en) | Methods of utilizing projectiles | |
| US4625618A (en) | Electromagnetic rail gun system and cartridge therefor | |
| CN110566365B (en) | Mode-switchable solid combined engine and missile | |
| CN109361154B (en) | Self-excitation type jet flow spark igniter | |
| CN111359125B (en) | Electromagnetic ejection fire extinguishing bomb for high-rise fire extinguishment | |
| WO2020073683A1 (en) | Separable combined range-extending system and method for aircraft | |
| CN107654347B (en) | A kind of high-performance solid ablative-type protective coating pulsed plasma electric propulsion device | |
| CN211626280U (en) | Four-duct propelling type small missile | |
| CN114320662A (en) | Wide-speed-range high-power-driven air-breathing combined propulsion power system and missile | |
| CN113932662A (en) | Adjustable cavitator structure with wing-shaped adjusting sheet for projectile entering water | |
| CN203177742U (en) | Software-attached sticky shocker | |
| CN205642187U (en) | Flying type explosive destroys ware | |
| US5042359A (en) | Projectile accelerating device | |
| CN111156864A (en) | Bullet bottom separation mass-reducing range-extending cannonball | |
| CN2765641Y (en) | Novel fire-extinguishing bomb and its emission device | |
| CN102878040A (en) | Magnetically controlled plasma power generation booster | |
| CN211626279U (en) | Bullet bottom separation mass-reducing range-extending cannonball | |
| CN216668430U (en) | Electronic weapon and launching magazine thereof | |
| CN209978713U (en) | Induction type electromagnetic catapult and fire engine | |
| CN115822814B (en) | Coaxial annular multi-electrode electric control solid thruster | |
| CN217686888U (en) | Whole-process control aircraft based on pulse attitude control engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |