CN106123688A - A kind of push away seat for the counter of rocket launching - Google Patents
A kind of push away seat for the counter of rocket launching Download PDFInfo
- Publication number
- CN106123688A CN106123688A CN201610556545.XA CN201610556545A CN106123688A CN 106123688 A CN106123688 A CN 106123688A CN 201610556545 A CN201610556545 A CN 201610556545A CN 106123688 A CN106123688 A CN 106123688A
- Authority
- CN
- China
- Prior art keywords
- rocket
- seat
- wall
- counter
- cylinder
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
Abstract
The present invention relates to a kind of push away seat for the counter of rocket launching, including the end (1), wall (2), circular port (3) or zigzag mouth (4), chamber (5), cylinder (7).The wall (2) of the anti-cylinder (7) pushing away seat (11) is tightly connected with the end (1), form chamber (5), the lower end of rocket (8) is placed on the counter of level and pushes away in seat (11), the anti-seat (11) that pushes away is coaxial with rocket (8), counter push away in the ground that seat (11) stretches into level below by stake fixed thereto, and and ground between sturdy；It is provided with cover seat (13) in the periphery of rocket lower end, is used for preventing thermal current (9) from burning out rocket (8).The present invention utilizes the anti-seat (11) that pushes away of the wall (2) newly increased to have collected rocket (8) transmitting kinetic energy to the thermal current (9) of the high pressure of surrounding level ejection, it is stored in chamber (5), it is changed into the energy of rocket of boosting, thus more energy efficient, rocket can be made to alleviate quality.
Description
Technical field
The present invention relates to a kind of push away seat for the counter of rocket launching.
Background technology
Rocket is to spray backward at a high speed with thermal current, utilizes the proal jet-propulsion plant of counteracting force produced.
Its own carries incendiary agent and oxidant, the oxygen and aiding combustion being independent of in air, both can fly in outer space again in an atmosphere
OK.Rocket is along with the consumption of propellant in flight course, and its quality constantly reduces, and is variable mass flying body.Modern fire
Arrow as sounding, launch a man-made satellite., manned spaceship, the vehicle of space station, and the booster of other aircraft.Launch
The rocket of satellite is generally three grades, and first order thrust is very big, and vertical ascent section can obtain effective speed and height, existing
After rocket is initially lighted a fire, the thermal current of the high pressure of rocket ejection is all to spray on a horizontal ground, and the thermal current of its ejection is all
Below rocket nozzle, the ground along level exhales to surrounding, and the counteracting force of transmitting also divides to surrounding the most greatly
Shedding, rocket does not make full use of the propulsive thrust from ground vertically upward of maximum, this flat with level ground
Push away seat for counter, there is the propulsive thrust shortcoming to surrounding radiological dispersal, cause the energy dissipation of a large amount of incendiary agent and oxidant burning,
And make the quality of rocket increase.
It addition, rifle and big gun are all that then rum point is fiery fried, and gases at high pressure are at rifle at some gunpowder of bullet (shell) bottom
In thorax or bore produce kinetic energy, release bullet, its bore or bore be all one end closing steel pipe, when bullet (or shell) from
During shooting mouth (or gun muzzle), the high pressure draught in bore (or bore) discharges suddenly, and bullet (or shell) also is become subtracting from acceleration
Speed, produces sudden change, sends explosive sound.Bullet described here (or shell) itself without burning incendiary agent and oxidant, its
Technical theme is different from the inventive technique theme of the present invention, and the present invention is the THR REV launched about jet-propulsion plant.
Therefore, it is necessary to develop a kind of the counter of the rocket launching both with the biggest propulsive thrust to push away seat；Have again without sudden change quick-fried
Fried sound, the counter of rocket launching making rocket be unlikely to unexpected speed change pushes away seat.
Summary of the invention
For solving the problems referred to above, it is an object of the invention to provide the counter of a kind of rocket launching and push away seat, start in rocket launching
Time, the propulsive thrust of rocket can be made full use of, be unlikely to again to produce when rocket launching the explosive sound of sudden change, make the acceleration of rocket
Uniformly, unexpected deceleration is occurred without.
The object of the present invention is achieved like this:
A kind of push away seat for the counter of rocket launching, in the lower section of rocket, a horizontal field realize, it is characterised in that: bag
Include the end, wall, circular port or zigzag mouth, chamber, cylinder.The wall of described cylinder was connected the end of with, forms chamber, the lower end of rocket is placed on water
Flat counter pushing away in seat, counter to push away seat coaxial with rocket, counter push away connection below seat and has vertical fixing stake, and the place of level is stretched in stake
In, and and horizontal field between sturdy；
The upper port horizontal cross-section of the described anti-wall pushing away seat is circular, bigger than rocket section, and it is peripheral to be enclosed within rocket, under
Part is outwards swelled for described chamber, for accepting and accommodate the thermal current of the high pressure that rocket sprays；
One end edge seal of the described anti-feather edge and the anti-wall pushing away seat pushing away seat connects as one；The described anti-seat that pushes away is with fiery
Arrow or rocket nozzle coaxial.
The described anti-wall cutting perpendicularly pushing away seat, is one zigzag after flattening, in order to gradually discharge the anti-intracavity pushing away seat
The pressure of thermal current of high pressure, and be unlikely to produce the pinking of sudden change.
Described rocket (8) and counter pushing away are provided with the cover seat coaxial with rocket between a upper port, cover seat comprises cover seat shell, cover seat
The end, nozzle bore.For the thermal current of high pressure is separated with rocket, in case the thermal current of high pressure burns rocket.
The invention has the beneficial effects as follows:
This apparatus structure is simple, can be collected from surrounding by the thermal current of the high pressure that rocket booster sprays, push away counter
Build pressure in the inner chamber of seat, and change the direction of the thermal current of ejection high pressure, base oneself upon on level ground, and retro-rocket
Lower surface, thus fully increase the propulsive thrust of rocket；After using cutting perpendicularly, and it is shown laid flat in the upper of the zigzag anti-wall pushing away seat
Port, makes the air-flow of the anti-high pressure pushing away an inner chamber gradually discharge, and on the one hand reduces transmitting noise；On the other hand adding of rocket is made
Speed is excessive gently, is unlikely to velocity jump.
Accompanying drawing explanation
Fig. 1 is that the counter of rocket launching of the present invention pushes away a first kind of way structural representation.
Fig. 2 is that the counter of rocket launching of the present invention pushes away a second way structural representation.
Fig. 3 is that the counter of rocket launching of the present invention pushes away the third mode structural representation of seat.
Fig. 4 is that the counter of rocket launching of the present invention pushes away the 4th kind of mode structural representation of seat.
Fig. 5 is that the counter of rocket launching of the present invention pushes away a fifth procedure structural representation.
Fig. 6 is that the counter of rocket launching of the present invention pushes away the 6th kind of mode structural representation of seat.
Fig. 7 is that the counter of rocket launching of the present invention pushes away the 7th kind of mode structural representation of seat.
Fig. 8 is that the counter of rocket launching of the present invention pushes away the 8th kind of mode structural representation of seat.
Fig. 9 is the expanded view of the wall of the anti-circular mouth pushing away seat of rocket launching of the present invention in Fig. 1, Figure 11 and Fig. 4-8.
Figure 10 is the expanded view of the wall of the anti-zigzag mouth pushing away seat in Fig. 2 and Fig. 3.
Figure 11 is the structural representation of the anti-cover seat being enclosed within rocket pushing away seat of rocket launching of the present invention.
Detailed description of the invention
Fig. 1 is in order to see that inside cuts the anti-structure chart pushing away seat (11) of 1/4, the anti-seat (11) that pushes away is by the cylinder of little cylinder
(7) being placed in the wall (2) of large cylinder, two upper port annular wall connects, and closes, the lower port of wall (2) and the discoideus end
(1) edge seal connects, and rocket (8) is placed in cylinder (7), the nozzle (10) of the rocket circular port (3) in cylinder (7) and the end
(1) between, and rocket (8), cylinder (7), wall (2) and the end (1) are coaxial；By cylinder (7), circular port (3), between wall (2) and the end (1)
Space be chamber (5)；First the thermal current (9) of the high pressure that rocket (8) nozzle initially sprays fills chamber (5), then in chamber (5)
Building up pressure, the thermal current (9) of the most a small amount of high pressure upwards leaks between rocket (8) and cylinder (7), but due to rocket
(7) amount of the thermal current (9) of nozzle (10) ejection high pressure is very big, and speed is quickly, so the thermal current of the high pressure in chamber (5)
(9) pressure will be also to gradually rise, when the pressure of the thermal current (9) of savings high pressure in chamber (5) reach a certain height,
Reverse push arrow (8) of getting angry is raised above, at this moment the thermal current (9) of the high pressure that the nozzle (10) of rocket (8) sprays be continuously replenished because of
The volume in the space that rocket (8) penetrates from chamber (5) and increases, makes the pressure in chamber (5) be continuously increased, so that rocket is upwards
Accelerate launch, this rocket projector, due to when rocket (8) depart from cylinder (7) upper port time, between cylinder (7) and rocket (7)
Gap increases suddenly, and thermal current (9) instantaneous burst of the high pressure in substantial amounts of chamber (5) is gone out, and produces loud noise, now will send
The acceleration of rocket also will diminish suddenly.In order to prevent this sudden change, this is improved by Fig. 2.
In Fig. 2, rocket (8) directly it is placed in the cylindrical wall (2) of band zigzag mouth (4), and the lower end of wall (2) is used
The end (1), is sealed, and cylinder (7) is coaxial with rocket (8), stays gap less between cylinder (7) and rocket (8) as far as possible.When rocket (8) be transmitted into by
During zigzag mouth (4) to be left, owing to the gas leakage gap between zigzag mouth (4) and rocket (8) is to be gradually increased from bottom to top
, so the pressure that its gas leakage makes the thermal current (9) of the high pressure in chamber (5) will not diminish, the most just in moment thus release suddenly
It is the unexpected change not having thermal current, also would not produce quick-fried sound.Owing to the space in this anti-chamber (5) pushing away seat (11) is the least,
When firing a rocket, it is impossible to gather the thermal current (9) of substantial amounts of high pressure, and relax the initial velocity of transmitting, make initial velocity not moment become
Speed, it is therefore proposed that the technical scheme shown in Fig. 3.
In Fig. 3, the upper port of the anti-cylinder (7) pushing away seat (11) is zigzag mouth (4), and cylinder (7) is the upper part of wall (2)；Wall
(2) bottom is divided into billiard table shape, and its lower end is coaxially connected with the edge at the end (1) of level, the lower part of wall (2) and the end (1)
And be chamber (5) between rocket (8).
In Fig. 4, in addition to the upper end of cylinder (7) is circular port (3), other structure is identical with Fig. 3.
In Fig. 5, being to be removed by the cylinder (7) in Fig. 3, the lower part of the most remaining wall (2), other is identical with Fig. 3.
In Fig. 6, counter push away the wall (2) that seat (11) is truncated cone-shaped, the lower port of the wall (2) of truncated cone-shaped and the discoideus end (1)
Closing envelope mutually to connect, rocket (8) is with counter to push away seat (11) coaxial, and the lower end of rocket (8) is placed at the end (1).
In Fig. 7, counter pushing away the wall (2) that seat (11) is cone, upper end round mouth is big, lower end point, and rocket (8) coaxial vertically-arranged,
The lower port of rocket (8) is placed in the cylinder of cone, and underground vertically imbedded by the cylinder of cone.
In Fig. 8, counter pushing away the wall (2) that seat (11) is inverted truncated cone-shaped, upper port is than the diameter of a circle at the end (1) of lower end
Greatly, described rocket (8) is placed at the end (1) of lower end, and with described counter to push away seat (1) coaxial.
In Fig. 9, the anti-wall (2) pushing away seat (11) as shown in Fig. 1, Fig. 4 is rectangle after launching.
In Figure 10, the anti-wall (2) pushing away seat (11) as shown in Figure 2 and Figure 3 is saw blade-shaped after launching.
The anti-end (1) pushing away seat (11) of Fig. 1～Fig. 6, extends vertically into sturdy level with vertical stake (12), stake (12)
Below ground, counter pushes away seat (11) in order to fixing.
Fig. 7, Fig. 8, Figure 11 are without fixing stake (12), directly the anti-seat (11) that pushes away can be fixed on below ground, and instead
The axle pushing away seat (11) is perpendicular to horizontal plane.
The above end (1) pushing away seat (11) for rocket launching counter, is all sturdy with ground, fixing, and horizontal positioned can
In one end of fixing vertically below at least one pile of the end (1), then stake is embedded vertically in horizontal field, is used for preventing from launching
The anti-axle center skew pushing away seat (11) during rocket (8).The most anti-periphery pushing away seat (11) of metal material and the end (1) are arranged
Yu Shuizhong so that fire a rocket (8) time cooling.
Owing to flat rocket launching place to be improved to the anti-seat that pushes away of wall (2) of band sealed type, utilize the storage collected
The thermal current kinetic energy of high pressure that sprays of the nozzle (10) of rocket (8) change direction after, rocket of boosting (8), make full use of
The energy that rocket (8) sprays, thus more energy efficient, fuel and the oxidant of rocket (8) when arranging, can be saved, alleviate rocket
(8) quality.
In Figure 11, during for preventing rocket (8) from launching, burn from the thermal current (9) of the anti-high pressure pushing away and returning up seat (11)
Ruining rocket (8), be set to leave the cover of nozzle bore (15) by the periphery of the rocket lower end in Fig. 1～8, this cover is referred to as rocket
(8) cover seat (13), coaxial with rocket (8), it is characterised in that: described cover seat (13) is by the cylindrical body (16) of upper part, centre
Wall (17) coaxial combination of the cover seat bottom (14) of part and the downward tubaeform or tubular of the mouth of lower part is integral；Cover seat
(13) upper part cylindrical body (16) entangles the lower part of rocket (8) from the lower end of rocket (8), and leave between rocket (8) every
The gap of heat；And in the inside of wall (2)；The lower edge of described cylindrical body (16) is connected with the edge seal of cover seat bottom (14)；
Described cover seat bottom (14) be arranged above with the nozzle bore (15) corresponding with the nozzle of rocket (8) (10), for through high pressure
Thermal current (9)；The cylindrical body (16) of the upper part of described cover seat (13) entangles the lower part of rocket (8), by the thermal current of high pressure
(9) separate with rocket (8), in case the thermal current of high pressure (9) burns rocket (8)；Described rocket (8) is located in cover seat bottom (14)
On, cover seat bottom (14) is plate shaped, or is provided with and prevents rocket (8) from moving horizontally, and corresponding with rocket portion concavo-convex
Face.On the one hand after rocket (8) is launched, utilize that the anti-thermal current (9) pushing away the high pressure that seat (11) returns is counter pushes away cover seat bottom (14)；Another
Aspect cover seat bottom (14) freely can depart from rocket (8), and cover seat (13) is because the effect of gravity is fallen down.
The bottom of cover seat (13) is divided into the wall (17) of the tubaeform or tubular downward with mouth, described tubaeform or tubular
The upper port of wall (17) is connected with the edge seal of the cover seat bottom (14) of described cover seat (13), is used for collecting and reflexive pushes away seat (11)
The most backward on the function of thermal current (9) of high pressure.
The ultimate principle of the present invention, principal character and advantages of the present invention have more than been shown and described.The technology of the industry
Personnel are it should be appreciated that the present invention is not restricted to the described embodiments, and what above-described embodiment and description described simply illustrates this
Bright principle, on the premise of the scope without departing from spirit of the present invention, the present invention also has various changes and modifications, these changes
Both fall within the scope of protection of present invention with improvement.Claimed scope by appending claims and etc.
Effect thing defines.
Claims (12)
1. push away a seat for the counter of rocket launching, a horizontal field realize, it is characterised in that: include the end (1), wall (2), circle
Shape mouth (3) or zigzag mouth (4), chamber (5), cylinder (7), the wall (2) of described cylinder (7) was connected with the discoideus end (1), formed chamber
(5), the lower end of rocket (8) being placed on the counter of level and pushes away in seat (11), the anti-seat (11) that pushes away is coaxial with rocket (8), counter pushes away seat
(11) being directly embedded under level ground, or have vertical fixing stake below, stake is stretched in the place of level, and with horizontal field it
Between sturdy；
The upper port horizontal cross-section of the described anti-wall (2) pushing away seat (11) is circular, bigger than rocket section, and is enclosed within outside rocket
Enclosing, bottom is divided into described chamber (5) outwards to swell, and is used for accepting to close the thermal current accommodating the high pressure that described rocket (8) sprays；
The edge at the described anti-end (1) pushing away seat (11) connects as one with one end edge seal of the described anti-wall (2) pushing away seat；
The described anti-seat (11) that pushes away is coaxial with rocket (8) or rocket nozzle (10)；
Described anti-wall (2) cutting perpendicularly pushing away seat (11), is one zigzag after flattening, in order to gradually discharges and described counter pushes away seat
(11) pressure of the thermal current (9) of the high pressure in chamber (5), and it is unlikely to produce the pinking of sudden change.
A kind of push away seat for the counter of rocket launching, it is characterised in that: by the described cylinder of little cylinder
(7) being placed in the described wall (2) of large cylinder, two upper port annular wall are tightly connected, and the lower port of wall (2) is discoideus with described
The end (1) peripheral sealing connect, described rocket (8) is placed in cylinder (7), the nozzle of the rocket circular port (3) in cylinder (7) with
At at the end (1), and rocket (8), cylinder (7), wall (2) and the end (1) they are coaxial.
A kind of push away seat for the counter of rocket launching, it is characterised in that: described rocket (8) directly stands
It is placed in the cylindrical wall (2) of described band zigzag mouth (4), and the lower end of wall (2) is with the peripheral sealing of described discoideus (1) even
Connect；Described cylinder (7), leaves gap between the end (1) and rocket (8), and coaxially.
A kind of push away seat for the counter of rocket launching, it is characterised in that: the upper port of described cylinder (7)
For zigzag mouth (4), described cylinder (7) is the upper part of wall (2)；The bottom of wall (2) is divided into billiard table shape, its lower end and level
The peripheral sealing at the discoideus end (1) connects.
The most according to claim 1 described a kind of push away seat for the counter of rocket launching, it is characterised in that: the top of described wall (2)
Being divided into the cylinder (7) of circular port (3), bottom is divided into billiard table shape；Wall (2) lower limb of billiard table shape and the week of the described discoideus end (1)
While be tightly connected.
The most according to claim 1 described a kind of push away seat for the counter of rocket launching, it is characterised in that: the wall of described billiard table shape
(2) lower limb is connected with the peripheral sealing at the discoideus end (1).
A kind of push away seat for the counter of rocket launching, it is characterised in that: under the wall (2) of described shape
Port is connected with the edge seal at the end (1) of plate shape.
A kind of push away seat for the counter of rocket launching, it is characterised in that: the described anti-seat (11) that pushes away is for circle
The wall (2) of taper, upper end round mouth is big, and lower end point, with described rocket (8) coaxial vertically-arranged, the lower end of rocket (8) is placed on cone
In the cylinder of wall (2), underground vertically imbedded by the cylinder of described cone-shaped wall (2).
A kind of push away seat for the counter of rocket launching, it is characterised in that: the described anti-seat (11) that pushes away is for falling
The wall (2) of the truncated cone-shaped put, upper end round mouth is bigger than the diameter of a circle at the end (1) of lower end, and described rocket (8) is placed on the end of lower end
(1) on, and with counter to push away seat (1) coaxial.
A kind of push away seat for the counter of rocket launching, it is characterised in that: the described end (1) is with flatly
Face is sturdy, fixes, with the end (1), the stake (12) being connected below, is embedded in the end (1) horizontal field below, is used for preventing at least one
Only fire a rocket (8) time the anti-axle center skew pushing away seat (11).
11. a kind of push away seat for the counter of rocket launching, it is characterised in that: described rocket (8) pushes away with counter
It is provided with the cover seat (13) coaxial with rocket (8) between the upper port of seat (11)；Described cover seat (13) is by the cylindrical body of upper part
(16), wall (17) coaxial combination of the cover seat bottom (14) of mid portion and the downward tubaeform or tubular of the mouth of lower part becomes one
Body；The upper part cylindrical body (16) of cover seat (13) entangles the lower part of rocket (8) from the lower end of rocket (8), and between rocket (8)
Leave heat insulation gap, and in the inside of wall (2)；The lower edge of described cylindrical body (16) and the edge seal of cover seat bottom (14)
Connect, described cover seat bottom (14) be arranged above with the nozzle bore (15) corresponding with the nozzle of rocket (8) (10), be used for through height
The thermal current (9) of pressure；The cylindrical body (16) of the upper part of described cover seat (13) is enclosed within the lower part of rocket (8), by the heat of high pressure
Air-flow (9) separates with rocket (8), in case the thermal current of high pressure (9) burns rocket (8)；Described rocket (8) is located in cover seat bottom
(14), on, cover seat bottom (14) is that flat board is circular；Or be provided with and prevent rocket (8) from moving horizontally, and relative with bottom rocket
The concavo-convex planar answered.
12. push away seat according to a kind of described in claim 11 for the counter of rocket launching, it is characterised in that: under described cover seat (13)
Part with the wall (17) of the downward tubaeform or tubular of mouth, the edge of the upper port of described wall (17) and described cover seat bottom (14)
Be tightly connected, be used for collecting reflexive push away seat (11) the most backward on the function of thermal current (9) of high pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610556545.XA CN106123688A (en) | 2016-07-10 | 2016-07-10 | A kind of push away seat for the counter of rocket launching |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610556545.XA CN106123688A (en) | 2016-07-10 | 2016-07-10 | A kind of push away seat for the counter of rocket launching |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106123688A true CN106123688A (en) | 2016-11-16 |
Family
ID=57283303
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610556545.XA Pending CN106123688A (en) | 2016-07-10 | 2016-07-10 | A kind of push away seat for the counter of rocket launching |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106123688A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107144171A (en) * | 2017-07-05 | 2017-09-08 | 李宏江 | Rocket launching saves assist device |
| CN109900478A (en) * | 2019-03-18 | 2019-06-18 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles rocket thrust test device and test method |
| CN110002008A (en) * | 2019-01-25 | 2019-07-12 | 北京蓝箭空间科技有限公司 | Vehicle and gas retro-rocket |
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| CN1279392A (en) * | 2000-02-20 | 2001-01-10 | 谢怀杰 | Energy-saving launcher for rocket or missible and energy saving calculation method |
| US20050172611A1 (en) * | 2004-02-09 | 2005-08-11 | James Blodgett Keith E. | Sinuous chevron exhaust nozzle |
| CN202063261U (en) * | 2011-04-06 | 2011-12-07 | 丛洋 | Gas-powered rocket and gas-powered rocket system |
| CN103994695A (en) * | 2013-02-18 | 2014-08-20 | 刘祖学 | Compensating energy-gathered launcher |
| CN104864774A (en) * | 2015-05-25 | 2015-08-26 | 北京理工大学 | Self-catapulting launching device for guided missile |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4796510A (en) * | 1987-11-09 | 1989-01-10 | General Dynamics, Pomona Division | Rocket exhaust recirculation obturator for missile launch tube |
| CN1279392A (en) * | 2000-02-20 | 2001-01-10 | 谢怀杰 | Energy-saving launcher for rocket or missible and energy saving calculation method |
| US20050172611A1 (en) * | 2004-02-09 | 2005-08-11 | James Blodgett Keith E. | Sinuous chevron exhaust nozzle |
| CN202063261U (en) * | 2011-04-06 | 2011-12-07 | 丛洋 | Gas-powered rocket and gas-powered rocket system |
| CN103994695A (en) * | 2013-02-18 | 2014-08-20 | 刘祖学 | Compensating energy-gathered launcher |
| CN104864774A (en) * | 2015-05-25 | 2015-08-26 | 北京理工大学 | Self-catapulting launching device for guided missile |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107144171A (en) * | 2017-07-05 | 2017-09-08 | 李宏江 | Rocket launching saves assist device |
| CN110002008A (en) * | 2019-01-25 | 2019-07-12 | 北京蓝箭空间科技有限公司 | Vehicle and gas retro-rocket |
| CN109900478A (en) * | 2019-03-18 | 2019-06-18 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles rocket thrust test device and test method |
| CN109900478B (en) * | 2019-03-18 | 2020-09-25 | 西安爱生技术集团公司 | Device and method for testing rocket thrust of small and medium-sized unmanned aerial vehicles |
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Application publication date: 20161116 |
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