CN107218857A - Micro missile - Google Patents
Micro missile Download PDFInfo
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- CN107218857A CN107218857A CN201710654877.6A CN201710654877A CN107218857A CN 107218857 A CN107218857 A CN 107218857A CN 201710654877 A CN201710654877 A CN 201710654877A CN 107218857 A CN107218857 A CN 107218857A
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- liquid
- oxidizer
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- oxidant
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The present invention relates to mechanical engineering technical field, more particularly, to a kind of micro missile.The micro missile includes：Body and the solid fuel and liquid oxidizer being arranged in body；High-temperature fuel gas is generated when solid fuel and liquid oxidizer react to burn, high-temperature fuel gas promotes body transmitting.The micro missile that the present invention is provided, its oxidant uses liquid oxidizer, solid-liquid engine has than leaping high, the easy regulation of longevity of service, thrust the characteristics of, so that guided missile has larger range, that is, because oxidant is liquid, fuel is solid, the burning of solid-liquid rocket is diffusion combustion, and burn rate is slower, and the reactive combustion time continues longer.Simultaneously because liquid oxidizer has higher energy, the propellant of solid-liquid rocket has higher-energy, power sufficient for a long time can be provided for body, and then extend body range.
Description
Technical field
The present invention relates to mechanical engineering technical field, more particularly, to a kind of micro missile.
Background technology
Micro missile is used to hit the small slow target such as LAV, unmanned plane and infantry detachment.Micro missile is because of its chi
Very little small, lightweight, generally applicable the features such as be convenient for carrying, be particularly suitable for use in individual combat.
Micro missile is built-in to have fuel and oxidant, and igniter makes fuel and oxidant reaction produce power to promote
MISSILE LAUNCHING.The power of micro missile in correlation technique uses solid form, that is, the fuel and oxidant of guided missile are
Solid forms, in both reactive combustions, the fuel of solid-state and the oxidant of solid-state react rapidly completely, and its reaction time is short,
The power time provided for guided missile is short, and the range of guided missile is shorter, it is impossible to the target of strike farther out.
To sum up, the range of the micro missile in correlation technique is shorter.
The content of the invention
It is an object of the invention to provide a kind of micro missile, to solve the range of micro missile present in prior art
Shorter technical problem.
A kind of micro missile that the present invention is provided, the micro missile includes：Body and it is arranged in the body
Solid fuel and liquid oxidizer；High temperature combustion is generated when the solid fuel and the liquid oxidizer react to burn
Gas, the high-temperature fuel gas promotes body transmitting.
Further, the micro missile also includes catalytic bed and drive division；Set gradually from front to back in the body
There are the driving cabin being sequentially communicated, oxidizer compartment, catalysis cabin and fuel compartment；The drive division is arranged in the driving cabin；Institute
Liquid oxidizer is stated to be arranged in the oxidizer compartment；The catalytic bed is arranged in the catalysis cabin；
The liquid oxidizer is hydrogen peroxide；The drive division is used to drive the liquid oxidizer to enter the catalysis
Bed；The catalytic bed is used for liquid oxidizer catalysis generation high-temperature gas H2O and O2。
Further, the drive division is gas cylinder；
Gases at high pressure are provided with the gas cylinder；Oxidant storage tank is provided with the oxidizer compartment；The liquid
Oxidant is arranged in the oxidant storage tank；The rear end of the oxidant storage tank is provided with the oxidation connected with the catalysis cabin
Agent is exported；The front end of the oxidizer compartment is provided with gases at high pressure import.
Further, the micro missile also includes the time relay and controller；
Valve is provided with the oxidant outlet；The valve is used to opening or closing the oxidant outlet；Institute
Valve and the time relay is stated to electrically connect with the controller；The controller is used to control the flow of the valve big
It is small.
Further, the micro missile also includes connecting tube；One end of the connecting tube connects with the oxidant outlet
Logical, the other end is connected with the catalysis cabin；The valve is arranged in the connecting tube.
Further, in the body, positioned at the rear end of the fuel compartment, it is provided with Servo-controller；Before the body
End is provided with control system on guidance camera and bullet；The Servo-controller, the guidance camera on the bullet with controlling
System electrical connection processed；Control system is used to control the Servo-controller on the bullet.
Further, it is provided with thermal insulation layer on the inwall of the fuel compartment.
Further, the rear end of the body is provided with the jet pipe connected with the fuel compartment.
Further, in the body, the front end positioned at the driving cabin is provided with warhead.
Further, on the bullet set-up of control system in the front end of the warhead.
The micro missile that the present invention is provided, sets solid fuel and liquid oxidizer, fixed fuel and liquid in body
Oxidant, which reacts to burn, generates high-temperature fuel gas, and the high-temperature fuel gas promotes body transmitting.
The micro missile that the present invention is provided, its oxidant uses liquid oxidizer, and solid-liquid engine has than leaping high, working
The characteristics of time length, thrust are easily adjusted so that guided missile has larger range, that is, because oxidant is liquid, fuel is solid
Body, the burning of solid-liquid rocket is diffusion combustion, and burn rate is slower, and the reactive combustion time continues longer.Simultaneously because liquid
Oxidant has higher energy, and the propellant of solid-liquid rocket has higher-energy, can be provided for body for a long time
Sufficient power, and then extend body range.The micro missile that the present invention is provided is applied to individual combat, is also applied for unmanned plane
Weapon is carried, available for the small slow target such as attack enemy army's LAV, unmanned plane and infantry detachment, it is adaptable to fight-terrorism warfare etc. compared with
Low earthquake intensity battlefield.
Brief description of the drawings
, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical scheme of the prior art
The accompanying drawing used required in embodiment or description of the prior art is briefly described, it should be apparent that, in describing below
Accompanying drawing is some embodiments of the present invention, for those of ordinary skill in the art, before creative work is not paid
Put, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation of micro missile provided in an embodiment of the present invention；
Fig. 2 is the sectional view of the micro missile shown in Fig. 1；
Fig. 3 is the partial structural diagram of the micro missile shown in Fig. 2；
Fig. 4 is another partial structural diagram of the micro missile shown in Fig. 2.
Reference：
1- bodies；2- solid fuels；3- liquid oxidizers；
4- gas cylinders；5- oxidant storage tanks；6- catalytic beds；
7- guides camera；Control system on 8- bullets；9- warheads；
10- empennages；11- jet pipes；12- Servo-controllers.
Embodiment
Technical scheme is clearly and completely described below in conjunction with accompanying drawing, it is clear that described implementation
Example is a part of embodiment of the invention, rather than whole embodiments.Based on the embodiment in the present invention, ordinary skill
The every other embodiment that personnel are obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
In the description of the invention, it is necessary to explanation, term " " center ", " on ", " under ", "left", "right", " vertical ",
The orientation or position relationship of the instruction such as " level ", " interior ", " outer " be based on orientation shown in the drawings or position relationship, merely to
Be easy to the description present invention and simplify description, rather than indicate or imply signified device or element must have specific orientation,
With specific azimuth configuration and operation, therefore it is not considered as limiting the invention.In addition, term " first ", " second ",
" the 3rd " is only used for describing purpose, and it is not intended that indicating or implying relative importance.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can
To be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, with concrete condition above-mentioned term can be understood at this
Concrete meaning in invention.
Fig. 1 is the structural representation of micro missile provided in an embodiment of the present invention；Fig. 2 is the micro missile shown in Fig. 1
Sectional view；Fig. 3 is the partial structural diagram of the micro missile shown in Fig. 2；Fig. 4 is another office of the micro missile shown in Fig. 2
Portion's structural representation, as shown in Figures 1 to 4, a kind of micro missile provided in an embodiment of the present invention, micro missile include：Body 1
And it is arranged on solid fuel 2 and liquid oxidizer 3 in body 1；When solid fuel 2 reacts with liquid oxidizer 3
Burning generation high-temperature fuel gas, high-temperature fuel gas promotes body 1 to launch.
Micro missile provided in an embodiment of the present invention, sets solid fuel 2 and liquid oxidizer 3, fixed combustion in body 1
Material and liquid oxidizer 3, which react to burn, generates high-temperature fuel gas, and the high-temperature fuel gas promotes body 1 to launch.
The micro missile that the present invention is provided, its oxidant uses liquid oxidizer 3, and solid-liquid engine has than leaping high, work
Make the characteristics of time length, thrust are easily adjusted so that guided missile has larger range.That is, because oxidant is liquid, fuel is
Solid, the burning of solid-liquid rocket is diffusion combustion, and burn rate is slower, and the reactive combustion time continues longer.Simultaneously because liquid
State oxidant has higher energy, and the propellant of solid-liquid rocket has higher-energy, when can provide long for body 1
Between sufficient power, and then extend the range of body 1.The micro missile that the present invention is provided is applied to individual combat, is also applied for nothing
People's air weapon, available for small slow targets such as attack enemy army's LAV, unmanned plane and infantry detachments, it is adaptable to fight-terrorism warfare
Etc. relatively low earthquake intensity battlefield.
Wherein, solid fuel 2 and the reactive combustion of liquid oxidizer 3 can be caused by igniter fire, can also pass through catalysis
The mode of oxidation is by solid fuel 2 and the reactive combustion of liquid oxidizer 3.
Preferably, solid fuel 2 is using high-performance solid fuel 2.Liquid oxidizer 3 can be hydrogen peroxide, nitric acid, four
Nitrous oxide etc..
As shown in Figures 1 to 4, on the basis of above-described embodiment, further, micro missile also includes the He of catalytic bed 6
Drive division；The driving cabin being sequentially communicated, oxidizer compartment, catalysis cabin and fuel compartment are disposed with body 1 from front to back；Drive
Dynamic portion is arranged in driving cabin；Liquid oxidizer 3 is arranged in oxidizer compartment；Catalytic bed 6 is arranged in catalysis cabin；Liquid oxidatively
Agent 3 is hydrogen peroxide；Drive division is used to drive liquid oxidizer 3 to enter catalytic bed 6；Catalytic bed 6 is used to urge liquid oxidizer 3
Metaplasia is into high-temperature gas H2O and O2。
In the present embodiment, the driving cabin being sequentially communicated, oxidizer compartment, catalysis cabin are disposed with body 1 from front to back
And fuel compartment；Drive division is arranged in driving cabin；Liquid oxidizer 3 is arranged in oxidizer compartment；Catalytic bed 6 is arranged on catalysis
In cabin；Liquid oxidizer 3 is hydrogen peroxide.Drive division driving liquid oxidizer 3 enters catalytic bed 6, and catalytic bed 6 is by hydrogen peroxide
It is catalyzed as oxygen and aqueous vapor, oxygen and aqueous vapor incoming fuel cabin, the fixed fuel in fuel compartment is pyrolyzed in high-temperature gas, and with
Blending burning, generate high-temperature fuel gas, high-temperature fuel gas promote body 1 launch.That is, sparking mode is the catalytic ignition of catalytic bed 6.
In the present embodiment, liquid oxidizer 3 is set to hydrogen peroxide, and sent out by way of catalysis with solid fuel 2
Raw reaction, it is simple in construction.
Wherein, the long term storage, just of hydrogen peroxide can be achieved using long-time storage, pre-packaged technology in oxidant storage tank 5
The property taken and quick response requirement.
Further, catalytic bed 6 includes the structures such as liquid collecting cavity, liquid homogenizing plate, gas injection panel.
As shown in Figures 1 to 4, on the basis of above-described embodiment, further, drive division is gas cylinder 4；High pressure gas
Gases at high pressure are provided with bottle 4；Oxidant storage tank 5 is provided with oxidizer compartment；Liquid oxidizer 3 is arranged on oxidant storage tank 5
It is interior；The rear end of oxidant storage tank 5 is provided with the oxidant outlet connected with catalysis cabin；The front end of oxidizer compartment is provided with high pressure gas
Body import.
In the present embodiment, the gas in gas cylinder 4 enters in oxidizer compartment, and to the oxidant storage tank in oxidizer compartment
5 apply the active force towards fuel compartment, and the liquid oxidizer 3 that oxidant storage tank 5 is squeezed in deformation, oxidant storage tank 5 leads to
The rear end of peroxide agent storage tank 5 is entered in catalysis cabin, and the catalytic action of the catalytic bed 6 through being catalyzed in cabin produces oxygen and water
Gas, oxygen is entered to fuel combustion in fuel compartment.
In the present embodiment, drive division is set to gas cylinder 4, passes through the extruding oxygen of the gases at high pressure in gas cylinder 4
Agent storage tank 5 realizes the purpose of driving liquid oxidizer 3, safe and reliable, convenient use person's manipulation.Meanwhile, guided missile size is small, matter
Amount is light, is easy to carry and installs, it is adaptable to individual combat and the air weapon as SUAV.
Wherein, gas cylinder 4 can use composite, can mitigate weight, the pressure store of gas cylinder can be improved again.High pressure
The pressure of gas cylinder 4 can be 35MPa.Gas cylinder is connected by valve pipeline with oxidant storage tank 5, by valve pipeline control to oxidant
The squeeze pressure of storage tank 5.
On the basis of above-described embodiment, further, micro missile also includes the time relay and controller；Oxidant
Exit is provided with valve；Valve is used to opening or closing oxidant outlet；Valve and the time relay are electric with controller
Connection；Controller is used for the uninterrupted of control valve.
In the present embodiment, user can be by setting the time relay, the size of controller control valve door flow, to control
Oxidizer flow rate is supplied, so as to change hybrid rocket engine thrust size, to realize the control to missile flight.This reality
The multiple igniting of guided missile can also be realized by applying example, that is, when the gases at high pressure in gas cylinder 4 promote the squeezed fluid of oxidant storage tank 5
State oxidant 3 enters in catalysis cabin, is catalyzed through catalytic bed 6, in oxygen incoming fuel cabin, and the reactive combustion of solid fuel 2 is given birth to
Into high-temperature fuel gas, completion is once lighted a fire.After the default time, valve is closed in controller control so that liquid oxidizer 3 is not
Enter back into and catalysis generation oxygen is carried out in catalysis cabin.After preset time, controller can control to open valve, hydraulic pressure oxidant again
It is again introduced into catalysis cabin and carries out catalysis generation oxygen, and by fixed fuel reactive combustion, completes once to light a fire again.
In the present embodiment, the flowing of liquid oxidizer 3 is controlled by controller control valve door, to realize micro missile
Repeatedly igniting starts and change propulsive, and the optimization, range for missile trajectory are improved and the flexible control of missile flight has important work
With.
As shown in Figures 1 to 4, on the basis of above-described embodiment, further, micro missile also includes connecting tube；Even
One end of adapter is connected with oxidant outlet, and the other end is connected with catalysis cabin；Valve is arranged in connecting tube.
In the present embodiment, one end of connecting tube is connected with oxidant outlet, and the other end is connected with catalysis cabin, and valve is arranged on
In connecting tube.By setting connecting tube so that the part in body 1 is easy to connect, and space makes full use of.
As shown in Figures 1 to 4, on the basis of above-described embodiment, further, in body 1, after fuel compartment
End, is provided with Servo-controller 12；The front end of body 1 is provided with control system 8 on guidance camera 7 and bullet；Servo-controller 12,
Guidance camera 7 is electrically connected with control system on bullet 8；Control system 8 is used to control Servo-controller 12 on bullet.
In the present embodiment, Servo-controller 12 is set in body 1, the front end of body 1 is provided with guidance camera 7 and bullet
Upper control system 8；Servo-controller 12, guidance camera 7 are electrically connected with control system.Camera 7 is guided to shoot outside body 1
Image information, and by control system 8 is controlled according to the image information received on control system 8, bullet in the information transfer to bullet
Servo-controller 12, so as to adjust the action of the empennage 10 of micro missile, and then adjusts the overall state of flight of micro missile.
That is, guided missile receives picture signal or laser signal by the guidance camera 7 of front end, at the analysis of control system on bullet 8
After reason, control empennage 10 to act by Servo-controller 12, realize the pitching, driftage and rolling of guided missile.
In the present embodiment, the guidance system of guidance camera 7 and control system formation micro missile, so as to make miniature lead
Bullet is according to outside situation adjust automatically state of flight, it is possible to achieve " no matter after the transmitting " of guided missile, it is possible to increase the transmitting of guided missile
Efficiency simultaneously ensures accuracy at target.
On the basis of above-described embodiment, further, thermal insulation layer is provided with the inwall of fuel compartment.
In the present embodiment, set in fuel compartment the fixed fuel in thermal insulation layer, fuel compartment in reactive combustion temperature compared with
Height, thermal insulation layer can reduce the heat transfer between its inwall in fuel compartment, so as to avoid the inwall of fuel compartment by higher temperatures
Spend and be damaged, extend the service life of micro missile.
On the basis of above-described embodiment, further, the rear end of body 1 is provided with the jet pipe 11 connected with fuel compartment.
In the present embodiment, body 1 rear end set jet pipe 11, fixed fuel burnt in fuel compartment generation high temperature combustion
Gas sprays through jet pipe 11, and promotes body 1 to launch.
Wherein, jet pipe 11 is Laval nozzle 11, for by the heat energy of the high-temperature high-pressure fuel gas for generation of being burnt in combustion chamber
It is converted into kinetic energy.Acceleration constantly is expanded when high-temperature high-pressure fuel gas flow through jet pipe 11, is finally discharged with high speed from the exit face of jet pipe 11,
Produce thrust.The steady propulsion of low thrust solid-liquid rocket can be 30N, meet the power demand of guided missile high-speed flight.
On the basis of above-described embodiment, further, in body 1, the front end positioned at driving cabin is provided with warhead 9.
In the present embodiment, in body 1, the front end positioned at driving cabin is provided with warhead 9, the storage ammunition of warhead 9.
Warhead 9 is that the explosive and corresponding assembly that guided missile is carried are used to damage to striking target, and reaches the purpose of operation.Warhead 9
The front end of body 1 is placed in, explosive type can be the conventional explosive or other explosives of guided missile.The maximum weight of Preliminary design warhead 9
For 0.3kg.
As shown in Figures 1 to 4, on the basis of above-described embodiment, further, control system 8 is arranged on fight on bullet
The front end in portion 9.
In the present embodiment, control system on bullet 8 is arranged on to the front end of warhead 9, can so be facilitated with guiding camera 7
Connection so that the space in body 1 makes full use of, reduces the volume of body 1.
Finally it should be noted that：Various embodiments above is merely illustrative of the technical solution of the present invention, rather than its limitations；To the greatest extent
The present invention is described in detail with reference to foregoing embodiments for pipe, it will be understood by those within the art that：Its according to
The technical scheme described in foregoing embodiments can so be modified, or which part or all technical characteristic are entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the present invention technology
The scope of scheme.
Claims (10)
1. a kind of micro missile, it is characterised in that including：Body and the solid fuel being arranged in the body and liquid
Oxidant；
High-temperature fuel gas is generated when the solid fuel and the liquid oxidizer react to burn, the high-temperature fuel gas promotes bullet
Body is launched.
2. micro missile according to claim 1, it is characterised in that also including catalytic bed and drive division；
The driving cabin being sequentially communicated, oxidizer compartment, catalysis cabin and fuel compartment are disposed with the body from front to back；Institute
Drive division is stated to be arranged in the driving cabin；The liquid oxidizer is arranged in the oxidizer compartment；The catalytic bed is set
In the catalysis cabin；
The liquid oxidizer is hydrogen peroxide；The drive division is used to drive the liquid oxidizer to enter the catalytic bed；
The catalytic bed is used for liquid oxidizer catalysis generation high-temperature gas H2O and O2。
3. micro missile according to claim 2, it is characterised in that the drive division is gas cylinder；
Gases at high pressure are provided with the gas cylinder；Oxidant storage tank is provided with the oxidizer compartment；The liquid oxidatively
Agent is arranged in the oxidant storage tank；The rear end of the oxidant storage tank is provided with the oxidant connected with the catalysis cabin and gone out
Mouthful；The front end of the oxidizer compartment is provided with gases at high pressure import.
4. micro missile according to claim 3, it is characterised in that also including the time relay and controller；
Valve is provided with the oxidant outlet；The valve is used to opening or closing the oxidant outlet；The valve
Door and the time relay are electrically connected with the controller；The controller is used for the uninterrupted for controlling the valve.
5. micro missile according to claim 4, it is characterised in that also including connecting tube；One end of the connecting tube with
The oxidant outlet connection, the other end is connected with the catalysis cabin；The valve is arranged in the connecting tube.
6. micro missile according to claim 2, it is characterised in that in the body, positioned at the rear end of the fuel compartment,
It is provided with Servo-controller；The front end of the body is provided with control system on guidance camera and bullet；The Servo-controller, institute
Guidance camera is stated to electrically connect with control system on the bullet；Control system is used to control the Servo-controller on the bullet.
7. micro missile according to claim 2, it is characterised in that be provided with thermal insulation layer on the inwall of the fuel compartment.
8. micro missile according to claim 2, it is characterised in that the rear end of the body is provided with and the fuel compartment
The jet pipe of connection.
9. micro missile according to claim 6, it is characterised in that in the body, the front end positioned at the driving cabin,
It is provided with warhead.
10. micro missile according to claim 9, it is characterised in that set-up of control system is in the fight on the bullet
The front end in portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710654877.6A CN107218857A (en) | 2017-08-03 | 2017-08-03 | Micro missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710654877.6A CN107218857A (en) | 2017-08-03 | 2017-08-03 | Micro missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107218857A true CN107218857A (en) | 2017-09-29 |
Family
ID=59954398
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710654877.6A Pending CN107218857A (en) | 2017-08-03 | 2017-08-03 | Micro missile |
Country Status (1)
| Country | Link |
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| CN (1) | CN107218857A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139299A (en) * | 2018-09-10 | 2019-01-04 | 北京航空航天大学 | Double pump solid-liquid rocket |
| CN109521142A (en) * | 2019-01-07 | 2019-03-26 | 大连理工大学 | A kind of device and method for the measurement solid propellant velocity of sound under the conditions of pressure change |
| CN111322173A (en) * | 2020-02-25 | 2020-06-23 | 北京航空航天大学 | Solid-liquid rocket engine with annular column-shaped storage tank |
| CN113465454A (en) * | 2021-07-28 | 2021-10-01 | 成都星源飞思科技有限公司 | Multi-group independent control surface and tail wing assembly device installed on same projectile body section |
| CN114320662A (en) * | 2022-01-06 | 2022-04-12 | 中国人民解放军国防科技大学 | Wide-speed-range high-power-driven air-breathing combined propulsion power system and missile |
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| CN106194502A (en) * | 2016-07-15 | 2016-12-07 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139299A (en) * | 2018-09-10 | 2019-01-04 | 北京航空航天大学 | Double pump solid-liquid rocket |
| CN109521142A (en) * | 2019-01-07 | 2019-03-26 | 大连理工大学 | A kind of device and method for the measurement solid propellant velocity of sound under the conditions of pressure change |
| CN111322173A (en) * | 2020-02-25 | 2020-06-23 | 北京航空航天大学 | Solid-liquid rocket engine with annular column-shaped storage tank |
| CN111322173B (en) * | 2020-02-25 | 2021-09-24 | 北京航空航天大学 | Solid-liquid rocket engine with annular column-shaped storage tank |
| CN113465454A (en) * | 2021-07-28 | 2021-10-01 | 成都星源飞思科技有限公司 | Multi-group independent control surface and tail wing assembly device installed on same projectile body section |
| CN114320662A (en) * | 2022-01-06 | 2022-04-12 | 中国人民解放军国防科技大学 | Wide-speed-range high-power-driven air-breathing combined propulsion power system and missile |
| CN114320662B (en) * | 2022-01-06 | 2022-11-22 | 中国人民解放军国防科技大学 | Wide-speed-range high-maneuvering air-breathing type combined propulsion power system and guided missile |
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Application publication date: 20170929 |