CN116294839A - Low-cost safe self-destruction method for guided rocket - Google Patents
Low-cost safe self-destruction method for guided rocket Download PDFInfo
- Publication number
- CN116294839A CN116294839A CN202310572597.6A CN202310572597A CN116294839A CN 116294839 A CN116294839 A CN 116294839A CN 202310572597 A CN202310572597 A CN 202310572597A CN 116294839 A CN116294839 A CN 116294839A
- Authority
- CN
- China
- Prior art keywords
- self
- destruction
- instruction
- flight
- guided rocket
- 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
- 238000000034 method Methods 0.000 title claims abstract description 16
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 44
- 230000000977 initiatory effect Effects 0.000 claims abstract description 26
- 239000002360 explosive Substances 0.000 claims abstract description 15
- 238000002955 isolation Methods 0.000 claims abstract description 6
- 230000001960 triggered effect Effects 0.000 claims description 8
- 230000003111 delayed effect Effects 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims description 3
- 230000002159 abnormal effect Effects 0.000 description 4
- 235000015842 Hesperis Nutrition 0.000 description 3
- 235000012633 Iberis amara Nutrition 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001687 destabilization Effects 0.000 description 1
- 230000002028 premature Effects 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
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- 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
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a low-cost safe self-destruction method of a guided rocket, which is used for constructing a safe self-destruction device, comprising a flight control device, an isolating switch and a self-destruction initiating explosive device; an isolating switch is arranged between the flight control device and the self-destruction initiating explosive device to implement circuit physical isolation for circuit protection; a self-destruction strategy combining engine self-destruction and rudder bias self-destruction is adopted; and a flight control autonomous identification security control mode is adopted, and whether a self-destruction instruction is sent out is judged by identifying the current information of the projectile body in real time. The invention is applicable to self-destruction of the projectile body under the condition of attitude divergence or track deviation in the low-cost guided rocket flight test, and ensures the safety requirement of the navigation area.
Description
Technical Field
The invention belongs to the technical field of rockets, and particularly relates to a low-cost safe self-destruction method for a guided rocket.
Background
The safety of the flight test navigation area is easy to meet due to the fact that the range of the traditional guided rocket is relatively close, and therefore a safety self-destruction device is not generally configured. However, with the gradual improvement of performances such as the range capability of the guided rocket, the influence range of the flight test is gradually increased, and when abnormal conditions such as instability or track deviation occur to the projectile body in the flight process, certain potential safety hazards may be generated to personnel, equipment, buildings and the like on two sides of the navigation area, so that the self-destruction under the abnormal conditions is realized by adding a safety self-destruction system on the projectile, and the safety of the first area, the navigation area and the landing area in the flight process is ensured. As shown in fig. 2, the conventional large rocket safe self-destruction system generally comprises a safe command receiver, an antenna, a safe controller, a security mechanism, a self-destruction initiating explosive device system, a large ground safety control station and the like, and the self-destruction command is uploaded by the ground safety control station or the missile is autonomously judged and sent to the self-destruction command to implement safe self-destruction of the missile. The traditional large rocket safe self-destruction system has complex composition, large weight and high cost, and is not suitable for small-sized low-cost guided rockets.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a low-cost safe self-destruction method of a guided rocket, and a safe self-destruction device is constructed, wherein the safe self-destruction device comprises a flight control device, an isolating switch and a self-destruction initiating explosive system; an isolating switch is arranged between the flight control device and the self-destruction initiating explosive device to implement circuit physical isolation for circuit protection; a self-destruction strategy combining engine self-destruction and rudder bias self-destruction is adopted; and a flight control autonomous identification security control mode is adopted, and whether a self-destruction instruction is sent out is judged by identifying the current information of the projectile body in real time. The invention is applicable to self-destruction of the projectile body under the condition of attitude divergence or track deviation in the low-cost guided rocket flight test, and ensures the safety requirement of the navigation area.
The technical scheme adopted by the invention for solving the technical problems comprises the following steps:
step 1: constructing a safe self-destruction device;
the safety self-destruction device comprises a flight control device, an isolating switch and a self-destruction initiating explosive device; an isolating switch is arranged between the flight control device and the self-destruction initiating explosive device to implement circuit physical isolation for circuit protection;
step 2: a self-destruction strategy combining engine self-destruction and rudder bias self-destruction is adopted;
when the guided rocket actively flies, an engine self-destruction instruction and a rudder deflection self-destruction instruction are sent; if a self-destruction condition is triggered, a safety control mode is entered, a rudder deflection instruction is sent to an air rudder steering engine to enable the posture of a guided rocket to be aggravated and dispersed and fall to the ground, meanwhile, a flight control device sends a self-destruction pre-instruction, a disconnecting switch is activated to enable a circuit path to be formed between the flight control device and a self-destruction initiating system, the flight control device outputs the self-destruction initiating instruction again, the self-destruction initiating device activates current to detonate the self-destruction initiating system, the front end enclosure of an engine is cut or broken down to release pressure, energy is rapidly exhausted, and the flying away from an aviation zone is avoided;
when the guided rocket passively flies, only a rudder deflection self-destruction instruction is sent, and an engine self-destruction instruction is not sent; if the self-destruction condition is triggered, entering a safety control mode, and only sending an air rudder deflection command to aggravate the divergence of the posture of the guided rocket so as to enable the guided rocket to land through aerodynamic resistance;
step 3: the method comprises the steps of adopting a flight control autonomous identification security control mode, and judging whether to send out a self-destruction instruction by identifying the current information of the projectile body in real time, wherein the method is as follows;
the conditions for executing the self-destructing instruction include:
(1) Time conditions: executing the self-destruction instruction of the engine in the working stage of the engine, and delaying the self-destruction instruction for a certain time after the transmission in order to avoid the self-destruction to destroy the ground equipment in the head area; executing the rudder deflection self-destruction instruction in the whole time of the delayed flight;
(2) Posture instability: through the real-time attitude of the inertial measurement unit sensitive guided rocket in flight, if the attitude angle deviation is overlarge, namely continuously exceeds a set value, the attitude instability of the guided missile is judged, and the flight control performs autonomous judgment and sends out a self-destruction instruction;
(3) Range over-range: when the flight control judges that the flight distance of the guided rocket exceeds the hit target, if the flight distance continuously exceeds the theoretical range set value, the guided rocket is judged to fly over the range, and the flight control autonomously judges to send out a self-destruction instruction;
(4) Reverse fly-back: when the flight control judges that the flight direction of the guided rocket is the opposite direction, if the continuous back flight exceeds a set value, the guided rocket is considered to reversely back fly, and the flight control autonomously judges to send out a self-destruction instruction.
Preferably, the self-destruction instruction time is determined after a certain time is delayed after the self-destruction instruction time is launched according to the safe distance of the guided rocket.
The beneficial effects of the invention are as follows:
1. according to the invention, the self-destruction electric path is isolated and protected by the isolating switch, the isolating switch can be used for physically isolating the self-destruction path between the on-bullet electric path and the self-destruction initiating explosive system, so that the false ignition risk caused by abnormal current such as static electricity on the bullet can be effectively avoided, and the phenomenon that the initiating explosive self-destruction initiating explosive system is not triggered to work even if a self-destruction current signal is misemitted on the bullet can be ensured;
2. the invention adopts the original flying control device on the bullet to implement self-destruction control, and can automatically judge and directly send out self-destruction current signals through the flying control device;
3. on the premise of meeting the basic safety self-destruction and security functions, the invention effectively simplifies the safety self-destruction system composition, has simple on-bullet system composition, does not need to construct complex ground supporting equipment, greatly reduces the cost, and provides an effective way for the small-sized guided rocket low-cost safety self-destruction system. The scheme can meet the requirements of safety and low cost, and has good application prospects in the fields of small guided rockets, rocket projectiles and the like.
Drawings
FIG. 1 is a schematic diagram of a safe self-destruction scheme of the present invention.
Fig. 2 is a schematic diagram of a prior art safety self-destruction scheme for a large rocket.
Detailed Description
The invention will be further described with reference to the drawings and examples.
In order to solve the problem of the safety of a navigation area when abnormal conditions such as missile instability or track deviation occur in the flight process of the small low-cost guided rocket, the invention provides a safe self-destruction scheme suitable for the small low-cost guided rocket, which can meet the safe self-destruction requirement of the guided rocket in the flight process and can also meet the low-cost requirement of the guided rocket.
As shown in FIG. 1, the invention mainly comprises a flight control device, a disconnecting switch and a self-destroying initiating explosive device. The circuit is protected by arranging the isolating switch between the flight control device and the self-destruction initiating explosive system to implement circuit physical isolation, and the self-destruction device is not detonated even if the flight control device mistakenly sends self-destruction ignition current or current caused by static electricity occurs in the ground test process before rocket projectile launching, so that the safety of ground service work is ensured; after the rocket projectile is launched, setting a safety control condition in the software of the flight control device, and when the safety control condition is triggered, the flight control device automatically sends out an engine self-destruction or rudder bias self-destruction instruction to quickly consume energy, so that the guided rocket self-destruction is realized.
The invention adopts a self-destruction strategy combining engine self-destruction and rudder bias self-destruction. When the guided rocket actively flies, an engine self-destruction instruction and a rudder deflection self-destruction instruction are sent. If the self-destruction condition is triggered, the safe control mode is entered, a rudder deflection instruction is sent to an air rudder steering engine to enable the posture of the guided rocket to be aggravated and diverged, the guided rocket falls to the ground as soon as possible, meanwhile, a flight control device sends a self-destruction pre-instruction, a disconnecting switch is activated to enable a circuit path to be formed between the flight control device and a self-destruction initiating system, the flight control device outputs the self-destruction initiating instruction again, the self-destruction initiating device activates current to detonate the self-destruction device, the front end enclosure of the engine is cut or broken down to release pressure, energy is rapidly exhausted, and the flying away from an aviation zone is avoided. When the guided rocket passively flies, only a rudder deflection self-destruction instruction is sent, and an engine self-destruction instruction is not sent. If the self-destruction condition is triggered, the system enters a safety control mode, and only an air rudder deflection command is sent to enable the posture of the guided rocket to be aggravated and diverged, and the guided rocket is enabled to fall to the ground as soon as possible through aerodynamic resistance.
The invention adopts a flight control autonomous recognition and security control mode. And judging whether to send out a self-destruction instruction by identifying the current information of the projectile body in real time. The main self-destruction conditions include: (1) time conditions: the execution of the self-destruction instruction of the engine should be in the working stage of the engine, and the self-destruction instruction time should be delayed for a certain time after the transmission in order to avoid the premature self-destruction of the ground equipment in the head area. Generally, the rocket is determined according to the fact that the guided rocket flies out a certain safety distance. Executing the rudder deflection self-destruction instruction in the whole time of the delayed flight; (2) attitude destabilization: through the real-time attitude of the inertial measurement unit sensitive guided rocket in flight, if the attitude angle deviation is overlarge and continuously exceeds a certain condition, the attitude of the guided rocket is considered to be unstable, and the flight control performs autonomous judgment and sends out a self-destruction instruction; (3) range over-travel: when the flight control judges that the flight distance of the guided rocket exceeds a hit target, if the flight distance continuously exceeds a certain theoretical range, the guided rocket is considered to fly over the range, and the flight control autonomously judges to send out a self-destruction instruction; (4) reverse fly-back: when the flight control judges that the flight direction of the guided rocket is the opposite direction, if the guided rocket continuously flies back to a certain value, the guided rocket is considered to fly back, and the flight control autonomously judges to send out a self-destruction instruction.
Specific examples:
taking a certain guided rocket as an example, the guided rocket has the active section of flight time of 50s and the passive section of flight of 550s.
Step one: setting security measures
Based on the existing flight control device of a certain guided rocket, a safety initiating explosive device subsystem is installed at the front end socket of an engine: self-destructing cutting locks. And an isolating switch is arranged on the cable between the self-destruction cutting lock and the flight control to carry out physical isolation protection on the circuit.
Step two: setting self-destruction time and corresponding self-destruction measures
Setting that the guidance rocket cannot send a self-destruction instruction between taking off and 10s according to the flight height of the guidance rocket and the safety requirement of a head area; after triggering the self-destruction condition, the engine self-destruction and rudder bias self-destruction instruction is sent between 10s and 50 s; and 50s until the guided rocket falls to the ground, and only sending a rudder deflection self-destruction instruction after triggering a self-destruction condition. As shown in table 1 below:
TABLE 1 self-destruction time interval and self-destruction measure
| Sequence number | Time interval | Self-destruction measure |
| 1 | 0s~10s | Not sending self-destruction instructions |
| 2 | 10s~50s | Engine self-destruction instruction and rudder deflection self-destruction instruction |
| 3 | 50s~600s | Rudder bias self-destruction instruction |
Step three: setting self-destruction condition
Determining attitude angle judgment conditions of attitude instability according to the guided rocket flight deflection attitude and by considering a certain coefficient; and determining an overtravel or return flight judgment condition according to the precision of the landing point of the guided rocket and the deviation trajectory and by considering a certain coefficient. The actual determination judgment conditions and rudder bias self-destruction instructions of the guided rocket are shown in the following table 2;
the variables in table 2 are defined as follows:
among the three types of self-destruction, when the above deflection angles simultaneously meet the rudder deflection self-destruction instruction angle requirements in table 2, the rudder deflection realizes self-destruction.
Table 2 self-destruction judgement condition and rudder bias self-destruction instruction
Claims (2)
1. The low-cost safe self-destruction method for the guided rocket is characterized by comprising the following steps of:
step 1: constructing a safe self-destruction device;
the safety self-destruction device comprises a flight control device, an isolating switch and a self-destruction initiating explosive device; an isolating switch is arranged between the flight control device and the self-destruction initiating explosive device to implement circuit physical isolation for circuit protection;
step 2: a self-destruction strategy combining engine self-destruction and rudder bias self-destruction is adopted;
when the guided rocket actively flies, an engine self-destruction instruction and a rudder deflection self-destruction instruction are sent; if a self-destruction condition is triggered, a safety control mode is entered, a rudder deflection instruction is sent to an air rudder steering engine to enable the posture of a guided rocket to be aggravated and dispersed and fall to the ground, meanwhile, a flight control device sends a self-destruction pre-instruction, a disconnecting switch is activated to enable a circuit path to be formed between the flight control device and a self-destruction initiating system, the flight control device outputs the self-destruction initiating instruction again, the self-destruction initiating device activates current to detonate the self-destruction initiating system, the front end enclosure of an engine is cut or broken down to release pressure, energy is rapidly exhausted, and the flying away from an aviation zone is avoided;
when the guided rocket passively flies, only a rudder deflection self-destruction instruction is sent, and an engine self-destruction instruction is not sent; if the self-destruction condition is triggered, entering a safety control mode, and only sending an air rudder deflection command to aggravate the divergence of the posture of the guided rocket so as to enable the guided rocket to land through aerodynamic resistance;
step 3: the method comprises the steps of adopting a flight control autonomous identification security control mode, and judging whether to send out a self-destruction instruction by identifying the current information of the projectile body in real time, wherein the method is as follows;
the conditions for executing the self-destructing instruction include:
(1) Time conditions: executing the self-destruction instruction of the engine in the working stage of the engine, and delaying the self-destruction instruction for a certain time after the transmission in order to avoid the self-destruction to destroy the ground equipment in the head area; executing the rudder deflection self-destruction instruction in the whole time of the delayed flight;
(2) Posture instability: through the real-time attitude of the inertial measurement unit sensitive guided rocket in flight, if the attitude angle deviation is overlarge, namely continuously exceeds a set value, the attitude instability of the guided missile is judged, and the flight control performs autonomous judgment and sends out a self-destruction instruction;
(3) Range over-range: when the flight control judges that the flight distance of the guided rocket exceeds the hit target, if the flight distance continuously exceeds the theoretical range set value, the guided rocket is judged to fly over the range, and the flight control autonomously judges to send out a self-destruction instruction;
(4) Reverse fly-back: when the flight control judges that the flight direction of the guided rocket is the opposite direction, if the continuous back flight exceeds a set value, the guided rocket is considered to reversely back fly, and the flight control autonomously judges to send out a self-destruction instruction.
2. The method for safely and self-destructing the guided rocket in low cost according to claim 1, wherein the self-destructing instruction time is determined after a certain time is delayed after the launching according to the safe distance of the guided rocket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310572597.6A CN116294839A (en) | 2023-05-22 | 2023-05-22 | Low-cost safe self-destruction method for guided rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310572597.6A CN116294839A (en) | 2023-05-22 | 2023-05-22 | Low-cost safe self-destruction method for guided rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116294839A true CN116294839A (en) | 2023-06-23 |
Family
ID=86785350
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310572597.6A Pending CN116294839A (en) | 2023-05-22 | 2023-05-22 | Low-cost safe self-destruction method for guided rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116294839A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2216709C2 (en) * | 2001-05-17 | 2003-11-20 | Киселев Владимир Владимирович | Radio fuse accord-2k for salvo delayed action blasting of ammunition with optical-electron device acknowledging presence of target |
| CN105137875A (en) * | 2015-08-21 | 2015-12-09 | 湖北三江航天红峰控制有限公司 | Simulator flight safety monitoring method |
| CN109596012A (en) * | 2018-11-28 | 2019-04-09 | 中国空空导弹研究院 | A kind of cable-styled active Safety system of missile-borne aircraft cutting |
| CN115839287A (en) * | 2023-01-03 | 2023-03-24 | 东方空间(西安)宇航技术有限公司 | Rocket engine self-destruction device, rocket engine and rocket assembly method |
| CN115903875A (en) * | 2023-01-05 | 2023-04-04 | 北京航天众信科技有限公司 | Effective security control method for target attitude instability |
| CN115930699A (en) * | 2022-12-14 | 2023-04-07 | 上海宇航系统工程研究所 | Safety control device for sublevel landing area of solid carrier rocket |
-
2023
- 2023-05-22 CN CN202310572597.6A patent/CN116294839A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2216709C2 (en) * | 2001-05-17 | 2003-11-20 | Киселев Владимир Владимирович | Radio fuse accord-2k for salvo delayed action blasting of ammunition with optical-electron device acknowledging presence of target |
| CN105137875A (en) * | 2015-08-21 | 2015-12-09 | 湖北三江航天红峰控制有限公司 | Simulator flight safety monitoring method |
| CN109596012A (en) * | 2018-11-28 | 2019-04-09 | 中国空空导弹研究院 | A kind of cable-styled active Safety system of missile-borne aircraft cutting |
| CN115930699A (en) * | 2022-12-14 | 2023-04-07 | 上海宇航系统工程研究所 | Safety control device for sublevel landing area of solid carrier rocket |
| CN115839287A (en) * | 2023-01-03 | 2023-03-24 | 东方空间(西安)宇航技术有限公司 | Rocket engine self-destruction device, rocket engine and rocket assembly method |
| CN115903875A (en) * | 2023-01-05 | 2023-04-04 | 北京航天众信科技有限公司 | Effective security control method for target attitude instability |
Non-Patent Citations (1)
| Title |
|---|
| 中国大百科全书总编辑委员会《航空航天》编辑委员会等: "《防空导弹引信设计及仿真技术》", 中国大百科全书出版社, pages: 397 - 398 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6921147B2 (en) | Multimode unmanned aerial vehicle | |
| US11762099B2 (en) | System and methods for countering satellite-navigated munitions | |
| US6666401B1 (en) | Missile defense system with dynamic trajectory adjustment | |
| CN107132547A (en) | A kind of unmanned plane management-control method | |
| CN113406966B (en) | Unmanned aerial vehicle counter-braking method and unmanned aerial vehicle counter-braking system | |
| CN102384702A (en) | Method for intercepting aircrafts without collateral damage in unmanned way | |
| CN109596012A (en) | A kind of cable-styled active Safety system of missile-borne aircraft cutting | |
| CN210433868U (en) | Airborne guidable fire extinguishing bomb | |
| CN116294839A (en) | Low-cost safe self-destruction method for guided rocket | |
| KR102296963B1 (en) | Target drive System and method using Reusable flight testing target | |
| CN210433869U (en) | Airborne guidable gliding cruise fire extinguishing bomb | |
| CN210583455U (en) | Controllable guidance fire extinguishing bomb and fire extinguishing system | |
| USH485H (en) | Frangible target with hydraulic warhead simulator | |
| CN107870625B (en) | Unmanned helicopter airborne task manager | |
| CN112198895A (en) | Guidance and guidance battle cooperation system based on unmanned aerial vehicle and control method | |
| CN210242585U (en) | Cutting cable type active safety control device of missile-borne aircraft | |
| CN213555041U (en) | Emergency rescue bullet | |
| RU2814056C1 (en) | Method of damaging non-homogeneous distributed group object | |
| RU2690640C1 (en) | Method for protection of ground objects from missile device with non-autonomous telecontrol systems | |
| CN116198734A (en) | Air-based interception aircraft with guide head arranged at rear part of flight direction | |
| CN115597442A (en) | Individual soldier rocket projectile system based on laser field composite guidance | |
| RU2155316C1 (en) | Method for destruction of ballistic missile | |
| Gao et al. | Failure Mode Analysis of Terminal Guidance Projectile | |
| Yang et al. | Common terminal-sensitive submunition with function of blockade and control | |
| CN116147421A (en) | Towed hard-killing active protection weapon and launching method |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20230623 |