CN111238306A - Method for launching carrier rocket at large initial speed - Google Patents
Method for launching carrier rocket at large initial speed Download PDFInfo
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- CN111238306A CN111238306A CN202010069934.6A CN202010069934A CN111238306A CN 111238306 A CN111238306 A CN 111238306A CN 202010069934 A CN202010069934 A CN 202010069934A CN 111238306 A CN111238306 A CN 111238306A
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- rocket
- power vehicle
- vehicle
- speed
- wings
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- 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
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The invention relates to a method for lifting a carrier rocket off the ground at a larger initial speed, which comprises a power vehicle (1), a guide rail (5) and a rocket (6), wherein the rocket (6) is horizontally laid on the power vehicle (1), and the power vehicle (1) moves forwards along the guide rail (5). When the rocket (6) is launched, the pressure of air on the rocket wings (7) on two sides of the front part of the rocket (6) enables the rocket (6) to be quickly separated from the power vehicle (1) on one hand, and provides centripetal force for the steering of the rocket (6) on the other hand, so that the horizontal speed of the rocket (6) is converted into the ascending speed without loss; when the rocket (6) leaves the ground and rises, the initial speed is not zero, compared with the conventional launching mode, the rocket rises to the same height and reaches the same orbit speed, the fuel carried by the rocket (6) can be reduced, and the total mass of the rocket (6) is reduced.
Description
Technical Field
The invention relates to a method for launching a carrier rocket at a larger initial speed, in particular to a method for launching a carrier rocket which leaves the ground at a larger initial speed.
Background
When the rocket is launched at present, the initial velocity of the rocket leaving the ground is zero. The increase in rocket speed and altitude requires the consumption of fuel carried by the rocket. Rocket engineers know that reducing the total mass of a rocket can bring great benefits, and therefore, they vomit the heart and drain blood, "jin Ji comparatively" and "two lian must contend".
Not only do there be ways to reduce the total mass of the rocket, but also ways to think about the rocket and the vehicle?
That is, the rocket is lifted off at a relatively high initial velocity.
When the initial velocity of the rocket leaving the ground is not zero, the carried fuel can be reduced, the total mass of the rocket can be reduced, and the launching benefit can be improved. The larger the initial velocity is, the more the total mass of the rocket can be reduced, and the launching benefit can be obviously improved.
The problem is how to achieve that the initial velocity of the rocket leaving the ground is not zero.
Disclosure of Invention
The invention aims to provide a method for lifting a carrier rocket off at a higher initial speed.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a method for lifting off a carrier rocket at a higher initial speed comprises a power vehicle, a guide rail and the rocket.
The guide rail is a seamless rail paved by linear steel rails.
The power of the motor vehicle is strong, and the motor vehicle can move along the guide rail.
The power vehicle is provided with a flame guide plate and a binding belt.
The transverse lower end surface of the flame guide plate is fixedly connected with the upper surface of a top plate close to the rear end of the power vehicle, and the included angle between the flame guide plate and the top plate in front of the flame guide plate is larger than 90 degrees.
The plurality of binding belts are respectively and fixedly arranged at the middle part of the motor vehicle along the longitudinal direction.
Two rocket wings are arranged on the rocket; the arrow wing is a flat plate; the two wing-shaped rocket bodies are respectively arranged at two sides of the front part of the rocket, the inner lateral surfaces of the two wing-shaped rocket bodies are respectively and fixedly connected with the outer surface of the rocket at corresponding positions, and when the rocket is in a horizontal state, the two wing-shaped rocket bodies are symmetrical to each other and have high front ends and low rear ends.
The rocket is laid on the top plate of the motor vehicle along the longitudinal direction when not being launched, the rear end of the rocket is close to the flame guide plate, and the middle part of the rocket is firmly bound on the motor vehicle by the plurality of binding belts.
The power vehicle carries the rocket from the initial point and moves along the guide rail in an accelerated way; when the speed of the power vehicle reaches the maximum value or the power vehicle moves at the maximum speed at a constant speed, a plurality of binding belts for binding the rocket are loosened at the same time, the rocket is ignited, the pressure of air on two rocket wings on the rocket enables the rocket to automatically lift head and ascend, and the rocket gradually changes to a vertical state in the ascending process; when the rocket is close to the vertical state, the two rocket wings are automatically separated from the rocket; when the rocket is ignited, the power vehicle starts to decelerate; after the rocket is lifted off, the power vehicle continues to do deceleration movement along the guide rail and then returns to the starting point.
The structure of the power vehicle roof plate has two preferable schemes.
A first preferred version of the structure of the power roof panel is such that it is an inclined panel that is inclined downwardly and rearwardly.
A second preferred version of the power roof panel construction is such that it is a horizontal panel.
The rocket rests longitudinally on the roof of the motor vehicle in such a way that the roof has a longitudinal groove in which the rocket lies.
After adopting such structure, the flame guide plate guides the flame ejected by the rocket to the rear upper part, thereby protecting the guide rail from ablation.
After the structure is adopted, when the rocket is close to a vertical state, the two rocket wings are automatically separated from the rocket, so that the resistance of air to the rocket is reduced.
After the structure is adopted, the power vehicle starts to decelerate while the rocket is ignited, so that the collision of a flame guide plate on the power vehicle to the tail end of the rocket is avoided.
After the structure is adopted, the rocket lies in the groove when not launched, thereby reducing the pressure born by the rocket.
After the structure is adopted, because the rocket wings are arranged on the rocket, the pressure of air on the rocket wings is generated when the rocket is launched, on one hand, the rocket is quickly separated from a power vehicle; on the other hand, the device provides centripetal force for rocket steering, so that the horizontal speed of the rocket is converted into ascending speed without loss. Two purposes are achieved at one stroke.
After the structure is adopted, the initial speed of the rocket is not zero when the rocket leaves the ground and is lifted off, compared with a conventional launching mode, the rocket is lifted to the same height and reaches the same orbit entering speed, fuel carried by the rocket can be reduced, and the total mass of the rocket is reduced; with the same fuel, the rocket rises at a greater altitude, or at a greater speed of entry.
After the structure is adopted, conditions are created for simplifying the rocket structure, such as canceling a binding booster at the lower part of the rocket.
Drawings
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
Figure 1 is a schematic side view of a method of launching a launch vehicle at a relatively high initial velocity.
Figure 2 is a schematic top view of a rocket.
Detailed Description
As shown in fig. 1 and fig. 2, a method for launching a launch vehicle at a relatively high initial speed includes a powered vehicle 1, a guideway 5, and a rocket 6.
As shown in fig. 1, the guide rail 5 is a seamless rail in which straight rails are laid.
As shown in fig. 1, the power of the vehicle 1 is strong and it can move along the guide rail 5.
As shown in fig. 1, the power vehicle 1 is mounted with a flame guide plate 2 and a binding band 4.
As shown in fig. 1, the flame guide plate 2 has a transverse lower end surface fixedly connected to the upper surface of the roof plate 3 near the rear end of the power vehicle 1, and has an angle greater than 90 ° with the roof plate 3 in front of it.
As shown in fig. 1, a plurality of tying bands 4 are respectively fastened and mounted in the middle of the motor vehicle 1 in the longitudinal direction.
As shown in fig. 1 and 2, two rocket wings 7 are mounted on the rocket 6; the arrow wing 7 is a flat plate; the two wing arrows 7 are respectively arranged at two sides of the front part of the rocket 6, the inner lateral surfaces of the two wing arrows 7 are respectively and fixedly connected with the outer surface of the rocket 6 at corresponding positions, when the rocket 6 is in a horizontal state, the two wing arrows 7 are symmetrical with each other, and the front ends are higher than the rear ends and lower than the rear ends.
As shown in fig. 1, the rocket 6, before being launched, is laid on the roof panel 3 of the power vehicle 1 in the longitudinal direction with its rear end near the flame guide panel 2 and its middle portion is firmly bound to the power vehicle 1 by the plurality of binding bands 4.
As shown in fig. 1, the power vehicle 1 carries the rocket 6 from the starting point and accelerates along the guide rail 5; when the speed of the power vehicle 1 reaches the maximum value or the power vehicle 1 moves at the maximum speed at a constant speed, a plurality of binding belts 4 binding the rocket 6 are loosened at the same time, the rocket 6 is ignited, the pressure of air on two rocket wings 7 on the rocket 6 enables the rocket 6 to automatically lift up and ascend, and the rocket is gradually changed into a vertical state in the ascending process; when the rocket 6 is close to the vertical state, the two rocket wings 7 are automatically separated from the rocket 6 to reduce the resistance of air to the rocket 6, and then the posture of the rocket 6 is controlled by itself; when the rocket 6 is ignited, the power vehicle 1 starts to decelerate so as to avoid the collision of a flame guide plate 2 on the power vehicle 1 to the tail end of the rocket 6; after the rocket 6 is lifted, the power vehicle 1 continues to perform deceleration movement along the guide rail 5 and then returns to the starting point.
There are two preferred configurations of the roof panel 3 of the motor vehicle 1.
A first preferable aspect of the structure of the roof panel 3 of the motor vehicle 1 is such that it is an inclined panel that is inclined rearward and downward.
In the first preferred scheme, after the rocket 6 is launched, the rocket 6 is converted into the vertical state for a short time, the time for the sprayed flame to act on the power vehicle 1 is short, the requirement on the ablation resistance of the top plate 3 on the power vehicle 1 is low, but the horizontal speed of the rocket 6 is not completely converted into the vertical speed in the process of converting the rocket 6 into the vertical state, and the scheme is adopted by reference.
As shown in fig. 1, a second preferred embodiment of the structure of the roof panel 3 of the motor vehicle 1 is such that it is a horizontal plate.
In the second preferred scheme, after the rocket 6 is launched, the rocket 6 is converted into the vertical state for a long time, the time of the ejected flame acting on the power vehicle 1 is long, the requirement on the ablation resistance of the top plate 3 on the power vehicle 1 is high, but the horizontal speed of the rocket 6 is easily converted into the vertical speed in the process of converting the rocket 6 into the vertical state, and the scheme is preferably adopted.
The rocket 6 rests longitudinally on the roof 3 of the motor vehicle 1 in such a way that the roof 3 has a longitudinal groove 8, the rocket 6 lying in the groove 8 to reduce the pressure to which the rocket 6 is subjected.
The embodiments of the present invention are described in detail above with reference to the accompanying drawings. The present invention is not limited to the above-described embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art. Variations that do not depart from the gist of the invention are intended to be within the scope of the invention.
Claims (4)
1. A method for lifting a carrier rocket off the ground at a larger initial speed comprises a rocket (6); the method is characterized in that:
the method for lifting the carrier rocket off at a larger initial speed also comprises a power vehicle (1) and a guide rail (5);
the guide rail (5) is a seamless rail paved by linear steel rails;
the power of the power vehicle (1) is strong and can move along the guide rail (5);
the power car (1) is provided with a flame guide plate (2) and a binding belt (4);
the transverse lower end face of the flame guide plate (2) is fixedly connected with the upper surface of a top plate (3) close to the rear end of the power vehicle (1), and the included angle between the flame guide plate and the top plate (3) in front of the flame guide plate is larger than 90 degrees;
a plurality of binding belts (4) are respectively and fixedly arranged at the middle part of the power vehicle (1) along the longitudinal direction;
two rocket wings (7) are arranged on the rocket (6); the arrow wing (7) is a flat plate; the two rocket wings (7) are respectively arranged at two sides of the front part of the rocket (6), the inner lateral surfaces of the two rocket wings (7) are respectively and fixedly connected with the outer surface of the rocket (6) at the corresponding position, when the rocket (6) is in a horizontal state, the two rocket wings (7) are symmetrical with each other, and the front ends are higher and the rear ends are lower;
the rocket (6) is laid on the top plate (3) of the power vehicle (1) along the longitudinal direction when not being launched, the rear end of the rocket is close to the flame guide plate (2), and the middle part of the rocket is firmly bound on the power vehicle (1) by the plurality of binding belts (4);
the power vehicle (1) carries the rocket (6) from the starting point and accelerates along the guide rail (5); when the speed of the power vehicle (1) reaches the maximum value, or when the power vehicle (1) moves at the maximum speed at a constant speed, a plurality of binding belts (4) for binding the rocket (6) are simultaneously loosened, the rocket (6) is ignited, and the air presses two rocket wings (7) on the rocket (6) to enable the rocket (6) to automatically lift and ascend and gradually change to a vertical state in the ascending process; when the rocket (6) is close to the vertical state, the two rocket wings (7) are automatically separated from the rocket (6); the vehicle (1) starts to decelerate while the rocket (6) is ignited; after the rocket (6) is lifted off, the power vehicle (1) continues to do deceleration movement along the guide rail (5) and then returns to the starting point.
2. A method of launching a launch vehicle at a relatively high initial velocity in accordance with claim 1, wherein:
the roof (3) of the motor vehicle (1) is an inclined plate inclined towards the rear lower direction.
3. A method of launching a launch vehicle at a relatively high initial velocity in accordance with claim 1, wherein:
the roof (3) of the power vehicle (1) is a horizontal plate.
4. A method of launching a launch vehicle at a relatively high initial velocity in accordance with claim 1, wherein:
the rocket (6) is longitudinally arranged on a top plate (3) of the motor vehicle (1) in a way that a longitudinal groove (8) is formed in the top plate (3), and the rocket (6) lies in the groove (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010069934.6A CN111238306A (en) | 2020-01-14 | 2020-01-14 | Method for launching carrier rocket at large initial speed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010069934.6A CN111238306A (en) | 2020-01-14 | 2020-01-14 | Method for launching carrier rocket at large initial speed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111238306A true CN111238306A (en) | 2020-06-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010069934.6A Pending CN111238306A (en) | 2020-01-14 | 2020-01-14 | Method for launching carrier rocket at large initial speed |
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| Country | Link |
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| CN (1) | CN111238306A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2083805A (en) * | 1932-11-22 | 1937-06-15 | Adams Herbert Luther | Launching device |
| US4014246A (en) * | 1975-07-02 | 1977-03-29 | All American Industries, Inc. | Rocket-powered apparatus for launching a flying device |
| US4709883A (en) * | 1985-04-22 | 1987-12-01 | Giuliani Robert L | Launch and ascent system |
| CN104192297A (en) * | 2014-09-24 | 2014-12-10 | 佛山市神风航空科技有限公司 | Short-distance passenger transportation equipment |
| CN105222646A (en) * | 2015-11-11 | 2016-01-06 | 隋广林 | A kind of high speed carrier loader and method realizing the horizontal transmitting of carrier rocket |
| AU2012101948A4 (en) * | 2012-06-26 | 2016-01-07 | John Scott | A method of launching an object |
| WO2017029566A1 (en) * | 2015-08-19 | 2017-02-23 | PIENAAR, Danie | Re-usable launch system and vehicle |
| CN106871723A (en) * | 2017-02-07 | 2017-06-20 | 国网技术学院 | Rise pocket emission system and its launch assist method |
| CN106989637A (en) * | 2017-04-30 | 2017-07-28 | 李宁 | A kind of rocket launching power assisting device |
-
2020
- 2020-01-14 CN CN202010069934.6A patent/CN111238306A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2083805A (en) * | 1932-11-22 | 1937-06-15 | Adams Herbert Luther | Launching device |
| US4014246A (en) * | 1975-07-02 | 1977-03-29 | All American Industries, Inc. | Rocket-powered apparatus for launching a flying device |
| US4709883A (en) * | 1985-04-22 | 1987-12-01 | Giuliani Robert L | Launch and ascent system |
| AU2012101948A4 (en) * | 2012-06-26 | 2016-01-07 | John Scott | A method of launching an object |
| CN104192297A (en) * | 2014-09-24 | 2014-12-10 | 佛山市神风航空科技有限公司 | Short-distance passenger transportation equipment |
| WO2017029566A1 (en) * | 2015-08-19 | 2017-02-23 | PIENAAR, Danie | Re-usable launch system and vehicle |
| CN105222646A (en) * | 2015-11-11 | 2016-01-06 | 隋广林 | A kind of high speed carrier loader and method realizing the horizontal transmitting of carrier rocket |
| CN106871723A (en) * | 2017-02-07 | 2017-06-20 | 国网技术学院 | Rise pocket emission system and its launch assist method |
| CN106989637A (en) * | 2017-04-30 | 2017-07-28 | 李宁 | A kind of rocket launching power assisting device |
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
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| CB02 | Change of applicant information |
Address after: No.66 Dongfeng Road, Liangshi Town, Shaodong City, Hunan Province 422800 Shaodong No.1 Middle School Applicant after: Li Xinya Address before: Room 1407, building 1, Baihe Jiayuan, No.113 Boai 7th Road, Torch Development Zone, Zhongshan City, Guangdong Province Applicant before: Li Xinya |