CN1299764A - Boosting rocket launching method of launching pad - Google Patents
Boosting rocket launching method of launching pad Download PDFInfo
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- CN1299764A CN1299764A CN 99124578 CN99124578A CN1299764A CN 1299764 A CN1299764 A CN 1299764A CN 99124578 CN99124578 CN 99124578 CN 99124578 A CN99124578 A CN 99124578A CN 1299764 A CN1299764 A CN 1299764A
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- rocket
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- launching
- launch pad
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000010304 firing Methods 0.000 claims description 7
- 230000001133 acceleration Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 2
- 239000000725 suspension Substances 0.000 claims description 2
- 235000015842 Hesperis Nutrition 0.000 abstract 1
- 235000012633 Iberis amara Nutrition 0.000 abstract 1
- 239000000446 fuel Substances 0.000 description 3
- 238000004804 winding Methods 0.000 description 2
- AWZOLILCOUMRDG-UHFFFAOYSA-N edifenphos Chemical compound C=1C=CC=CC=1SP(=O)(OCC)SC1=CC=CC=C1 AWZOLILCOUMRDG-UHFFFAOYSA-N 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 238000012857 repacking Methods 0.000 description 1
- 239000002760 rocket fuel Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
A booster rocket launching method of a launching pad belongs to the technical field of rockets. The problem of launching of the booster rocket of the launching pad is solved. The launching platform is driven by a driving system such as a jet engine or a linear motor, and the launching platform pushes the accelerating rocket firstly during launching, and the rocket is ignited to continue accelerating and lifting after obtaining a certain speed. Used for rocket launching.
Description
The invention belongs to the rocketry field.
The rocket launching method of using is that rocket is erected on the static launch pad now, and rocket is igniting when initial velocity is zero, leans on the thrust lift-off and the flight of rocket self driving engine entirely.The motion of rocket belongs to the varying accelerated motion of variable mass object.Because the mass ratio of rocket fuel and rocket is up to 90%, after the rocket firing, along with the burning of fuel, the rocket quality reduces thereupon.By Newton's second law as can be known, produce same acceleration/accel, rocket is when beginning to launch, and required thrust is ten times when flying at full speed; Therefore in the lift-off stage, it is very big to consume energy, and influences the raising of carrying capacity and flying speed.
The objective of the invention is: invent a kind of launch pad that allows earlier and boost rocket, make rocket obtain suitable speed after, allow rocket firing again, continue to quicken the booster rocket launching method for launching pad of lift-off.
Booster rocket launching method for launching pad as shown in drawings.Rocket [1] is vertically fixed on the launch pad [3] by buckle release [2], or vertically floats on launch pad [3].Launch pad [3] is with drive systems such as jet engine or linear motor or magnetic artillery.Launch pad [3] is contained in some the guide rails that are parallel to each other [6] of launch tower [7].Launch tower [7] has a vertical gap, and rocket [1] can enter launch tower [7] thus.Launch pad [3] is connected with missile transporting truck, and rocket [1] standing position is steadily placed on the launch pad [3].Launch tower [7] top is provided with lifting appliance, and rocket [1] also can be through lifting launch pad [3].Also has which floor workplatform in the middle of the launch tower [7].When firing a rocket, the drive system of starting launch pad [3] allows launch pad [3] earlier rocket [1] be promoted earlier; Regulate and control drive system then, launch pad [3] and solid (putting) rocket [1] are thereon quickened; When treating that rocket [1] stretches out launch tower [7], rocket [1] igniting, buckle release [2] is threaded off simultaneously or suitably in advance, drive system hysteresis rocket [1] the igniting appropriate time braking of launch pad [3], rocket [1] produces on the initial velocity basis in launch pad [3] boosting, and the thrust that produces by self driving engine continues to quicken lift-off again.
Advantage of the present invention is: 1, rocket obtains just to blast off behind certain initial velocity by the launch pad boosting, can save rocket with many fuel, favourable increase rocket voyage and carrying capacity; 2, can lack carrying fuel, carry volume or reduce the rocket volume thereby increase; But 3, launch pad drive system repeated use, thereby reduce launch cost.
Accompanying drawing shows the booster rocket launching method for launching pad scheme drawing.Among the figure: a---front view; B-birds-eye view; C---launch pad starting section; D---launch pad accelerating sections; E---launch pad braking, rocket dropout section; F---rocket firing point; 1---rocket; 2---buckle release; 3---launch pad; 4---the motor-driven limit of straight line electric; 5---the linear motor deckle; 6---guide rail; 7---launch tower; 8---power supply.
Realize that best way of the present invention is: the assist system of launch pad [3] preferably adopts several high-power linear asynchronous motors simple and reliable for structure.And the fuse moving limit [4] of linear asynchronous motor of motion of launch pad [3] is equipped with winding, and the deckle [5] of not adorning winding links to each other with launch tower [7].Linear motor is by the variable-frequency variable-voltage power supply power supply near launch tower [7].Be conceived to that exploitation is fast, small investment, research amount be little, the assist system of launch pad [3] also can be selected several high-power jet engines repackings for use.Launch tower [7] should be high as far as possible, so that farthest improve the initial velocity that has had before the boosting rocket firing at the end.Launch pad [3] preferentially adopts magnetic suspension to cooperate with guide rail [6], and next adopts track roller to cooperate.As with buckle release [2], adopt the automatic disconnecting gear of existing multi-stage rocket inter-stage.Starting, acceleration, the braking of launch pad [3] realize by the regulation and control drive system; The boosting process of whole launch pads [3] such as the regulation and control of drive system, rocket dropout is by the computer wired remote control.All controls of back of rocket firing beginning are all with existing rocket launching method.
Claims (5)
1, a kind of booster rocket launching method for launching pad, it is characterized in that: a, rocket [1] is vertically fixed on the launch pad [3] by buckle release [2], or vertically float on launch pad [3], b, launch pad [3] is with drive systems such as jet engine or linear motor or magnetic artillery, c, launch pad [3] is contained in some the guide rails that are parallel to each other [6] of launch tower [7], d, launch tower [7] has a vertical gap, rocket [1] can enter launch tower [7] thus, e, launch pad [3] is connected with missile transporting truck, rocket [1] standing position is steadily placed on the launch pad [3], f, launch tower [7] top is provided with lifting appliance, rocket [1] also can be through lifting launch pad [3], g, when firing a rocket, the drive system of starting launch pad [3] allows launch pad [3] earlier rocket [1] be promoted earlier; Regulate and control drive system then, launch pad [3] and solid (putting) rocket [1] are thereon quickened; When treating that rocket [1] stretches out launch tower [7], rocket [1] igniting, buckle release [2] is threaded off simultaneously or suitably in advance, drive system hysteresis rocket [1] the igniting appropriate time braking of launch pad [3], rocket [1] produces on the initial velocity basis in launch pad [3] boosting, and the thrust that produces by self driving engine continues to quicken lift-off again.
2, booster rocket launching method for launching pad according to claim 1 is characterized in that: linear motor is by the variable-frequency variable-voltage power supply power supply near launch tower [7].
3, booster rocket launching method for launching pad according to claim 1 is characterized in that: launch pad [3] preferentially adopts magnetic suspension to cooperate with guide rail [6], and next adopts track roller to cooperate.
4, booster rocket launching method for launching pad according to claim 1 is characterized in that: buckle release [2] adopts the automatic disconnecting gear of existing multi-stage rocket inter-stage.
5, booster rocket launching method for launching pad according to claim 1, it is characterized in that: starting, acceleration, the braking of launch pad [3], realize that by the regulation and control drive system boosting process of whole launch pads [3] such as the regulation and control of drive system, rocket dropout is by the computer wired remote control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB991245784A CN100344932C (en) | 1999-12-13 | 1999-12-13 | Boosting rocket launching method of launching pad |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB991245784A CN100344932C (en) | 1999-12-13 | 1999-12-13 | Boosting rocket launching method of launching pad |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1299764A true CN1299764A (en) | 2001-06-20 |
| CN100344932C CN100344932C (en) | 2007-10-24 |
Family
ID=5283486
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB991245784A Expired - Fee Related CN100344932C (en) | 1999-12-13 | 1999-12-13 | Boosting rocket launching method of launching pad |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100344932C (en) |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102689698A (en) * | 2012-05-22 | 2012-09-26 | 北京航空航天大学 | Ground emitting control device of solid-liquid powered aircraft |
| CN103541833A (en) * | 2012-07-10 | 2014-01-29 | 北京航天发射技术研究所 | Single-spray-pipe rocket combustion-gas stream drainage device |
| CN103542770A (en) * | 2012-07-10 | 2014-01-29 | 北京航天发射技术研究所 | Large launch platform with built-in water channel for protection and manufacturing method thereof |
| CN103542771A (en) * | 2012-07-10 | 2014-01-29 | 北京航天发射技术研究所 | Protection type cantilever launching platform with built-in water channel and manufacturing method thereof |
| CN103542772A (en) * | 2013-10-23 | 2014-01-29 | 北京航天发射技术研究所 | Thermal protection method for launch pad |
| CN103712522A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Rocket launching system with water spraying, cooling and denoising functions |
| CN103994691A (en) * | 2013-02-18 | 2014-08-20 | 刘祖学 | Novel launching device |
| 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 |
| CN105667835A (en) * | 2016-03-25 | 2016-06-15 | 济南环太机电技术有限公司 | Heavy lift launch vehicle catapult and ejection method thereof |
| CN105836152A (en) * | 2016-03-25 | 2016-08-10 | 济南环太机电技术有限公司 | Heavy-duty spacecraft ejection system and distributed energy storage central synchronized acting ejection method thereof |
| CN106240850A (en) * | 2016-08-17 | 2016-12-21 | 杨文清 | Spacecraft is transmitted back to be closed flat platform |
| CN107144171A (en) * | 2017-07-05 | 2017-09-08 | 李宏江 | Rocket launching saves assist device |
| CN107238320A (en) * | 2016-03-29 | 2017-10-10 | 熵零技术逻辑工程院集团股份有限公司 | A kind of structure accelerated method |
| CN107672823A (en) * | 2017-10-06 | 2018-02-09 | 廖忠民 | High in the clouds launching site |
| CN110406698A (en) * | 2019-07-24 | 2019-11-05 | 中国人民解放军海军工程大学 | A kind of space launch system propelled based on electromagnetism and method |
| WO2020244626A1 (en) * | 2019-06-06 | 2020-12-10 | 宋延军 | Assistance system for assisting launching and recovery of aircraft, and launching and recovery method |
| CN112896563A (en) * | 2021-02-26 | 2021-06-04 | 曹煜培 | Pulley block type rocket launching method and device |
| CN112945010A (en) * | 2021-04-02 | 2021-06-11 | 李新亚 | Method for launching carrier rocket by boosting high-pressure compressed gas |
| US11988172B2 (en) | 2020-11-19 | 2024-05-21 | Raytheon Company | Ignition safety device for a multi-pulse or multi-stage rocket motor system |
Families Citing this family (1)
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| CN107804472A (en) * | 2017-10-06 | 2018-03-16 | 廖忠民 | Express locomotive assist system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85105057A (en) * | 1985-07-04 | 1986-02-10 | 景尔强 | Magnetic emittor |
| CN2324697Y (en) * | 1998-03-09 | 1999-06-16 | 朱德明 | Moving-coil electromagnetic driving unit |
-
1999
- 1999-12-13 CN CNB991245784A patent/CN100344932C/en not_active Expired - Fee Related
Cited By (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102689698A (en) * | 2012-05-22 | 2012-09-26 | 北京航空航天大学 | Ground emitting control device of solid-liquid powered aircraft |
| CN103542771B (en) * | 2012-07-10 | 2015-07-15 | 北京航天发射技术研究所 | Protection type cantilever launching platform with built-in water channel and manufacturing method thereof |
| CN103541833A (en) * | 2012-07-10 | 2014-01-29 | 北京航天发射技术研究所 | Single-spray-pipe rocket combustion-gas stream drainage device |
| CN103542770A (en) * | 2012-07-10 | 2014-01-29 | 北京航天发射技术研究所 | Large launch platform with built-in water channel for protection and manufacturing method thereof |
| CN103542771A (en) * | 2012-07-10 | 2014-01-29 | 北京航天发射技术研究所 | Protection type cantilever launching platform with built-in water channel and manufacturing method thereof |
| CN103541833B (en) * | 2012-07-10 | 2015-11-25 | 北京航天发射技术研究所 | Single spraying pipe rocket gas flow row leads device |
| CN103542770B (en) * | 2012-07-10 | 2015-07-15 | 北京航天发射技术研究所 | Large launch platform with built-in water channel for protection and manufacturing method thereof |
| CN103712522B (en) * | 2012-09-29 | 2016-03-30 | 北京航天发射技术研究所 | A kind of rocket-firing system possessing spray cooling decrease of noise functions |
| CN103712522A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Rocket launching system with water spraying, cooling and denoising functions |
| CN103994691A (en) * | 2013-02-18 | 2014-08-20 | 刘祖学 | Novel launching device |
| CN103542772B (en) * | 2013-10-23 | 2015-09-16 | 北京航天发射技术研究所 | A kind of thermal protection method of transmitting station |
| CN103542772A (en) * | 2013-10-23 | 2014-01-29 | 北京航天发射技术研究所 | Thermal protection method for launch pad |
| 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 |
| CN105836152B (en) * | 2016-03-25 | 2017-12-05 | 济南环太机电技术有限公司 | Synchronous acting catapult technique is concentrated in heavy spacecraft ejection system and its scattered accumulation of energy |
| CN105667835A (en) * | 2016-03-25 | 2016-06-15 | 济南环太机电技术有限公司 | Heavy lift launch vehicle catapult and ejection method thereof |
| CN105836152A (en) * | 2016-03-25 | 2016-08-10 | 济南环太机电技术有限公司 | Heavy-duty spacecraft ejection system and distributed energy storage central synchronized acting ejection method thereof |
| CN107238320A (en) * | 2016-03-29 | 2017-10-10 | 熵零技术逻辑工程院集团股份有限公司 | A kind of structure accelerated method |
| CN106240850A (en) * | 2016-08-17 | 2016-12-21 | 杨文清 | Spacecraft is transmitted back to be closed flat platform |
| CN107144171A (en) * | 2017-07-05 | 2017-09-08 | 李宏江 | Rocket launching saves assist device |
| CN107672823A (en) * | 2017-10-06 | 2018-02-09 | 廖忠民 | High in the clouds launching site |
| WO2020244626A1 (en) * | 2019-06-06 | 2020-12-10 | 宋延军 | Assistance system for assisting launching and recovery of aircraft, and launching and recovery method |
| JP7251845B2 (en) | 2019-07-24 | 2023-04-04 | 中国人民解放軍海軍工程大学 | Space launch system and method based on electromagnetic propulsion |
| CN110406698B (en) * | 2019-07-24 | 2020-05-08 | 中国人民解放军海军工程大学 | Space launching system and method based on electromagnetic push launching |
| WO2021012729A1 (en) * | 2019-07-24 | 2021-01-28 | 中国人民解放军海军工程大学 | Space launch system and method based on electromagnetic pushing |
| KR20220020381A (en) * | 2019-07-24 | 2022-02-18 | 네이벌 유니버시티 오브 엔지니어링 | Space launch system and method based on electromagnetic pushing |
| JP2022542783A (en) * | 2019-07-24 | 2022-10-07 | 中国人民解放軍海軍工程大学 | Space launch system and method based on electromagnetic propulsion |
| CN110406698A (en) * | 2019-07-24 | 2019-11-05 | 中国人民解放军海军工程大学 | A kind of space launch system propelled based on electromagnetism and method |
| EP4005933A4 (en) * | 2019-07-24 | 2023-08-23 | Naval University of Engineering | Space launch system and method based on electromagnetic pushing |
| KR102690418B1 (en) * | 2019-07-24 | 2024-07-30 | 네이벌 유니버시티 오브 엔지니어링 | Space launch system and method based on electromagnetic pushing |
| US11988172B2 (en) | 2020-11-19 | 2024-05-21 | Raytheon Company | Ignition safety device for a multi-pulse or multi-stage rocket motor system |
| CN112896563A (en) * | 2021-02-26 | 2021-06-04 | 曹煜培 | Pulley block type rocket launching method and device |
| CN112945010A (en) * | 2021-04-02 | 2021-06-11 | 李新亚 | Method for launching carrier rocket by boosting high-pressure compressed gas |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100344932C (en) | 2007-10-24 |
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| C57 | Notification of unclear or unknown address | ||
| DD01 | Delivery of document by public notice |
Addressee: Xu Zhijun Document name: Notification of registration of the invention patent right |
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| C14 | Grant of patent or utility model | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20071024 Termination date: 20100113 |