CN102466429A - 宇宙火箭推力装置的改进方案 - Google Patents

宇宙火箭推力装置的改进方案 Download PDF

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CN102466429A
CN102466429A CN2011101849106A CN201110184910A CN102466429A CN 102466429 A CN102466429 A CN 102466429A CN 2011101849106 A CN2011101849106 A CN 2011101849106A CN 201110184910 A CN201110184910 A CN 201110184910A CN 102466429 A CN102466429 A CN 102466429A
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rocket
spaceship
thrust device
improved scheme
flying object
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吴佑之
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BEIJING KESHI MEDICAL IMAGE INSTITUTE OF TECHNOLOGY
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BEIJING KESHI MEDICAL IMAGE INSTITUTE OF TECHNOLOGY
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Priority to CN2011101849106A priority Critical patent/CN102466429A/zh
Publication of CN102466429A publication Critical patent/CN102466429A/zh
Priority to PCT/CN2012/000911 priority patent/WO2013004073A1/zh
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
    • B64G1/281—Spin-stabilised spacecraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/401—Liquid propellant rocket engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/84—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using movable nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Toys (AREA)

Abstract

本发明宇宙火箭推力装置的改进方案，是在宇宙飞船的运载火箭C和飞船A的外壁上，加装了几组喷火管E，用以随时调整飞船飞行轨迹的偏离程度。一方面可以节省宇宙飞船在发射之后调整航向所需的能源消耗，并可控制脱离了运载火箭C之后的飞船A的飞行状态。

Description

宇宙火箭推力装置的改进方案
技术领域
本发明专利宇宙火箭推力装置的改进方案，涉及到一种宇宙火箭的发射方式，以及在空气和在太空中飞行时的操控方法。
背景技术
目前，世界各大国在研制、和发射宇宙火箭时所采用的方法，全都是单一用一种轴向推进和施力控制飞行方向的方式、使飞行物升空，并在空气中、或在宇宙中飞行。把这种现象说得形象一点，就如同人们在用一根筷子顶住铅笔的底端、用杂耍的方式往上推一样。当飞行物在空气中、或在高空地球引力所还能达到的范围内飞行时，会时常出现一些不稳定的因素，(例如遇到大风的吹拂、或是遇到上升的气流、或是遇到高山和地球磁场的不均匀所引起的地心引力场的变化等)均会使飞行物偏离既定的飞行轨道。为了“纠偏”，各国目前还只是依靠随时不断地增减飞行物尾端四个喷火管D所喷射出的气流强度，来纠正航向。(近来世界各国的科学家可能已经意识到了这一点，作了“稍稍的改进”——即把四个发射筒径向地外移——“捆绑”在飞行物的外皮上)这样做，既不精确可靠，效率也低，同时也浪费了大量的燃料；而由于增添了这些众多的精密操控设备，也大大增加了飞行物的起飞重量，从而减少了飞行物内部空间的装载率。可以这样肯定地说，这种发射方式，还蕴含着极大的潜在风险，所以每个国家在“每一次”发射宇航器成功之后，都会毫无例外地要欢呼一下：“发射成功！”，这个奇怪现象，在所有其它的359个行业领域里，大概是“绝无仅有”的！别的行业仅仅是在第一次试制、试航、或是试飞成功时，才去“欢”庆一番。
发明内容
鉴于目前所采用的这种发射和飞行操控的方式相当复杂、风险也极大，而且浪费能量，现发明出一种依靠在飞行物圆筒外壁侧向施力的办法来控制航向。其具体措施是，在火箭和飞船尾部外壳的圆周上，安装几组(一组最少三个)朝火箭筒径向喷射的小喷火管E。(例如在运载火箭C的底部的外壁上安装一组，同时在飞船A的底部的外壁上也安装一组)当运载火箭C一旦脱离了飞船A之后，飞船A仍可自由地在太空中调整自身的飞行状态和运行轨道。
本发明之所以可能获得极高的发射和升空的成功率，其所依据的基本原理是：
1、原来的方案是，宇宙飞船一旦发射升空之后，为纠正飞行物的偏离，需稍稍“扭转”一下火箭前进的方向以纠偏，此时，需由运载火箭C底部的某个喷火管D多喷射出一些气流，(或稍稍抑制一下另一个喷火管D所喷出的气流)给飞行物造成一个扭矩，其扭矩的大小，约等于推进力的增量、(或减量)乘以飞行物圆筒的半径R；此外，其精确度也不好控制。
2、而本发明所采用的的方法是，在飞行物的侧向加装小喷火管E，为了纠偏，其径向喷射出的气流所产生的调整飞行物飞行方向的力矩，约等于推进力乘以飞行物重心离喷火管E的距离H。通常H值往往是飞行物圆筒半径R的十几倍，所以它产生出的扭矩，就比前者增大了一个数量级，也就是说，为修正航向所需的燃料，可以较前者减少了一个数量级。
3、经这样的改进之后，附带地还带来一个极为重要的优点：火箭尾部的发射筒，可以减少到仅存一个，这就大大简化了控制发射火力的一系列程序和机构。
附图说明
图1：系一般飞行物之侧视图
A——飞船
B——重心
C——飞行物之运载火箭部分
D——喷火管
图2：系增加了两组小喷火管之后的侧视图
E——小喷火管
具体实施方式
1、在宇宙飞船的运载火箭C的底部的上方，安装上一组(三个以上)径向喷火的小喷火管E；
2、在飞船A的外壳的尾端上，也安装上一组(三个以上)可径向喷火的小喷火管E。

Claims (2)

1.本发明专利宇宙火箭推力装置的改进方案，其特征是节省了宇宙飞船在发射之后调整航向所需的能源消耗，并可控制脱离了运载火箭C之后的飞船A的飞行方向。
2.根据权利要求1所述，在宇宙飞船的运载火箭C和飞船A的外壁上，加装几组径向喷火的小喷火管E。
CN2011101849106A 2011-07-04 2011-07-04 宇宙火箭推力装置的改进方案 Pending CN102466429A (zh)

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CN2011101849106A CN102466429A (zh) 2011-07-04 2011-07-04 宇宙火箭推力装置的改进方案
PCT/CN2012/000911 WO2013004073A1 (zh) 2011-07-04 2012-07-03 运载火箭推力装置

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013004073A1 (zh) * 2011-07-04 2013-01-10 北京科实医学图像技术研究所 运载火箭推力装置
CN105730682A (zh) * 2016-02-02 2016-07-06 毕国伟 多点矢量推力分布的主动式气动布局的飞机
CN111653174A (zh) * 2020-05-26 2020-09-11 南京航空航天大学 一种应用于科普教育的火箭模型稳定控制演示装置
WO2022068022A1 (zh) * 2020-09-30 2022-04-07 浙江大学 一种尾座式垂直起降无人机及其控制方法

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8998131B1 (en) * 2013-10-17 2015-04-07 The Boeing Company Differential throttling control enhancement

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JPH02117498A (ja) * 1988-10-25 1990-05-01 Nec Corp 人工衛星の軌道制御装置
US5064152A (en) * 1988-12-23 1991-11-12 Aerospatiale Societe Nationale Industrielle Method of determining and controlling the attitude of a spin-stabilized satellite in an elliptical transfer orbit
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013004073A1 (zh) * 2011-07-04 2013-01-10 北京科实医学图像技术研究所 运载火箭推力装置
CN105730682A (zh) * 2016-02-02 2016-07-06 毕国伟 多点矢量推力分布的主动式气动布局的飞机
CN111653174A (zh) * 2020-05-26 2020-09-11 南京航空航天大学 一种应用于科普教育的火箭模型稳定控制演示装置
WO2022068022A1 (zh) * 2020-09-30 2022-04-07 浙江大学 一种尾座式垂直起降无人机及其控制方法

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Application publication date: 20120523