CN101055164A - Rocket propulsion enhancing design - Google Patents
Rocket propulsion enhancing design Download PDFInfo
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- CN101055164A CN101055164A CN 200610108813 CN200610108813A CN101055164A CN 101055164 A CN101055164 A CN 101055164A CN 200610108813 CN200610108813 CN 200610108813 CN 200610108813 A CN200610108813 A CN 200610108813A CN 101055164 A CN101055164 A CN 101055164A
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- cylinder
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- high explosive
- thrust
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Abstract
The invention relates to a method for increasing rocket impellent which provides module combined multi-section ''high explosive cartridge'' to launch the rocket for increasing rocket launch speed and shot. The invention first uses ''conventional impellent gunpowder initial propelling booster'' to send bullet and the cartridge to high altitude more than 300 m, time difference percussion mechanism at bullet bottom detonates the high explosive in cartridge one by one in predetermined time difference, and then the high explosive detonates in high altitude, so that it can safely provides impellent greatly large than any solid or liquid propellant, therefore the rocket can fly very far distance, coupling with guide apparatus, to correctly get to object. The invention can be used for rigid body launch in military and space navigation.
Description
1, technical field:
The present invention relates to a kind of design that strengthens propelling force of rocket, can substantially increase the speed and the range of rocket, simple in structure, easy to operate, reduce weight and fuel consumption widely, belong to the rocket propulsion field.
2, background technology:
The application of rocket is very wide weary, but most the use at military aspect, from conventional meaning, rocket by it principle and when emission the energy source that advances, can be divided into " carrying out agent voluntarily " type and outside two kinds in the source that advances, the former propeller is in rocket inside, produce very high speed with emitting high compression gas, the promotion rocket travels forward, because propellant only can be for rocket provides a kind of quite limited accelerator, so the distance of hitting is quite limited; Latter's rocket is added emitter and is promoted, and this device also is to bring promotion with the guanidine of high compression gas or controlled combustion, all is the accelerator that has suitable high level generally, so striking distance can be far.More than two kinds of accurate control and monitoring that all relate to whole emission and hit process, need very complex apparatus and qualified technical staff, in the emission use, be full of potential dangerous consequences, make operating process extremely expensive, and limitation is arranged, and common people and mechanism can't make inquiries.Thereby, on more effective propulsion method, low-cost valency and easy to operate on, be the target that the scientific research personnel lays siege to always.
High explosive can not be made the purposes of thrust on ground, because it can be to object and personnel cause catastrophic consequence on every side.Do the air detonation very fast disappearance of stress wave under the air drag around but we can see in the high-altitude, can not cause any infringement following object and personnel.For example: the thunder and lightning air detonation of a minimum of nature also has the energy of the hiroshima bomb of suitable 20,000 tons of TNT equivalent tonne, but underperson and object are safety and sound, because it is minimum liftoff more than 200M.Therefore, be contained in the cylinder and make air detonation in the air if we only make ten kilograms of high explosives to thousands of kilograms of hundreds ofs at height, it not only produces thrust but also can guarantee that ground is perfectly safe so, certainly this cylinder must be lightweight can smashing material (as carbon nano-fiber resin etc.) thinking of the present invention that Here it is the basis.
The invention provides and a kind ofly can make up the method that " the high explosive cylinder " of dismounting fires a rocket arbitrarily with multi-segmental, high explosive is at the air detonation ripple of the spherical structure of the even rule of the aerial detonation generation of height in the cylinder, the a plurality of cylinder sections that can bring into play the propelling power that surpasses 1,100 times of any thrust gunpowder, combination safely can increase and decrease as required arbitrarily and reach any various overlength distance, and devices such as GPS, inertial navigation in the fin of bullet shell and the bullet guarantee the accurate direction of advance of bullet.Its volume is little, in light weight, with low cost, emission is convenient, and high mobility is arranged.
3, summary of the invention:
Purpose of the present invention is to propose that a kind of " the high explosive cylinder: replace conventional heavy complex structure again, expensive solid or liquid trust engine make the promotion part reach modularization and appoint the degree that makes up of needing with the modularization multi-segmental.
Of the present invention being achieved in that
A kind of cylinder rocket is by anterior bullet, and the middle part is a joint or a more piece high explosive cylinder, and portion is not " the initial boost motor of conventional thrust gunpowder " totally three part compositions, except that placing essential article, also has guidance control package in the bullet; The cylinder peripheral structure is by three component parts, on be the cylinder top board of middle webbing than book, that is to say the base plate of a joint cylinder, in be tube circle, under be the cylinder base plate, that is to say following one the joint top board, three screw connection mutually by more shallow screw thread mutually, can screw the mutual slippage in place under detonation wave (stress wave) effect, remaining at last top board is accepted thrust the front portion is advanced.High explosive and filler are arranged in the cylinder chamber, and each saves cylinder and sends the electric wire contact by " time difference percussion lock ", by predetermined time difference control, ignites high explosive in the tube by joint, generally is to be separated by 0.1-1 between second.
Cylinder is made with synthetic material, and as the carbon nano-fiber resinae, it is higher 70 times and weight is 1/7 of steel than hardness of steel, adiabatic good, high temperature resistant more than 2000 ℃, stretch modulus is more than the 310GPa, and the detonation pressure of TNT is 19GPa, and RDX (hexogen) is 33.8GPa.
Built-in high explosive of cylinder such as TNT or B explosive (TNT35%+RDX65%) etc. can be sphere or cylindricality, spherical medicine ball have vertical contact incident with become two kinds of angle slippage incident calculate and the cylindricality powder column mainly to be vertical incidence calculate.If the opinion with the TNT of sphere, its saturated degree of packing is with 1.7g/cm
3Meter (generally is 1.65g/cm
3) if its volume of 100kg dose W=58823cm
3, its straight warp
Add cylinder circle thickness, the cylinder overall diameter roughly has only about 1m, if high explosive is made columniform words, the cylinder diameter can also be more elongated.
In the cylinder during high explosive detonation, TNT finishes between the 7.4 microsecond amounts of center, stress wave reflects passing to the barrel inner face in several microseconds, be that a barrel quickens, the process of deformation failure, simultaneously also be the process of an energy accumulation, this increment to cartridge case top board thrust is good, and is called " barrel effect ", the barrel that synthetic material is forced more is thick more, and the increment of its effect is also just big more.
" the initial boost motor of conventional thrust gunpowder " is existing current techique, and this paper does not just give unnecessary details.
The establishment of an invention must be able to show its novelty and practicality, with have in the comparison of like product efficient, simplify, convenient, at a low price superiority.
Make the superiority that more coarse basic number reason calculation specifications the present invention is had with two comparison example:
Comparative example one:
Here " the high explosive cylinder " as thrust portion only one saves, and TNT explosive 50kg is arranged in the cylinder, adds cylindrical shell and weighs also in 50kg, then the heavy 100kg of a joint cylinder.Bullet is 150kg equally.After with " conventional thrust cartridge-type booster " rocket of weight 250kg being delivered to the 300m high-altitude earlier, then cylinder is ignited in time difference percussion lock.Boost motor is pushed away by cylinder detonation, itself weight and push away increment and can count.
Rocket speed formula according to Tsiolkovsky (to call Qi Shi in the following text):
V
1＝2.3VrLg(1+M
f/M
s)
M in the Qi Shi formula
fBe fuel mass, this is the quality 50kg of high explosive TNT.Promptly the cylinder shell 50kg of different rows can not count in the single-unit cylinder from ruining after fried.
M
sBeing the quality of fuel burning-out amount rocket shell, promptly is the weight of bullet 150kg here.
V
1For rocket injection speed at the end, promptly be the speed of detonation wave effect rocket warhead gained here.
V
rOriginally being that thrust powder burning gas at the end sprays end speed, promptly is high explosive detonation wave propagation velocity here, and the TNT explosion velocity is 7000m/s, if with B explosive (TNT0.4+RDX0.6) explosion velocity more than 8000m/s.
In the Qi Shi formula, improve Vr than improving M
f/ M
sMore effective
Cylinder rocket firing rate:
V
1＝2.3·7000XLG(150+50)/150＝16100·Lg1.333＝16100·0.1249＝2010.9m/s
The cylinder rocket is penetrated height: establish α=45 °
H＝(V
1 2/2g)·Sin
2α＝[(2010.9)
2/(2×9.8)]·Sin
245°＝(4044121/19.6)·(0.7)
2＝101103m
The cylinder rocket is penetrated far:
S＝(V
1 2/g)Sin2a＝(2010.9/9.8)·2Sinα·Cosα＝(4044121/9.8)·0.98·404412.1m＝404km
This shows that two kinds of methods that contrasted equally all are the bullets that advances heavy 150kg, former emission " bodyguard " the rocket thrust gross weight 575kg of portion, the cylinder rocket here has only 60kg, but firing rate is " bodyguard " 1.5 times, and penetrating far is " bodyguard " 2.2 times.
If, finish from " the initial boost motor of conventional thrust gunpowder " thrust with " time difference percussion lock " with two joint explosive cylinders, arrive more than the 300m, ignited 1 cylinder every 0.1 second, then:
First segment Va=2.3 * 7000 * Lg (150+50+100)/250=16100 * Lg1.2=16100 * 0.0792=1275.1m/s
The second joint V
b=2.3 * 7000 * Lg (150+50)/150=2010.9m/s
Get last rocket V=Va+Vb=1275.1+2010.9=3286m/s
Range: S=(V
2/ gSin2 α=[(3286)
2/ 9.8] * Sin2 α=1079779.6m=1080km
This shows that increased a cylinder again, the thrust portion gross weight is 200kg only, be that former bodyguard's rocket thrust portion gross weight is about 1/3, and firing rate is big 2.5 times, and 6 times of far firing ranges reach the requirement more than 1,000 kilometers of intermediate range missile.
These calculate certainly and calculate with theoretical property under the pure vacuum environment, and in fact " vertical asymptote " of air drag generation all do not taken into account.But because penetrating of it is tall and big, all flown most time of rocket more than 20km in the high above vacuum of stratosphere, the influence that air hinders is minimum.0.1 the guanidine at second interval is towards formula detonation, gravitational influence can be ignored.General speed can be done simple addition with the speed that two joints produce respectively.If saving, 3 joints, 4 add more than the cylinders that guidance device is done long-range and the intercontinental missile use is fully passable.Add that it is in light weight, modular cylinder combined and instant, the last one thousandth of conventional missile (just) with low cost can do long-range group bombardment as shell, and so-called costliness and be that the missile defense systems NMD of single antagonism will be in the status that is unable to cope with fully.
Comparative example two:
| No. 1 carrier rocket of the Long March: the heavy 81300kg of the heavy 300kg full weight of long 29.45m diameter 2.25m satellite 81600kg thrust portion penetrates high 400km (400000m) needs firing rate: H=(Vo 2/2g)·Sin 2α (if establish earlier α=90 °) 400000=[V 2/(2×9.8)]×Sin 290°V 2＝7840000 V＝2800M/Sec |
Also with conventional thrust gunpowder whole rocket was released high aerial of 300m before this.Satisfy one with time difference percussion lock then and ignite " high explosive cylinder " and have 2 cylinders, having TNT100kg to add cylindrical shell in every also is 100kg, the heavy 200kg of each cylinder.Bullet (satellite) is 300kg equally, penetrates height to the space of 400km, and its speed is calculated.
First V
1=2.3 * 7000 * Lg (300+200+100)/300=16100 * Lg1.2=1275.1m/s
Second V
2=2.3 * 7000 * Lg (300+100)/300=16100Lg1.333=2010.9m/s
V＝V
1+V
2＝1275.1+2010.9＝3286M/S
Speed is penetrated the high H=[(3286 that is)
2/ 298] Sin
290 °=550908m (550.9km)
This shows, if the part of neither meter " the initial boost motor of conventional thrust gunpowder ", emission 300kg satellite (bullet) only needs 2 of the cylinders of each 100kg, its whole carrier rocket full weight is 700kg, weight is 1/116th of No. 1 rocket of the Long March, penetrate high more than 500km, its rocket length is estimated the highest only about 3m, its module combined type high explosive cylinder structure, simply cheap, so its thrust portion total cost is several one thousandths of " Long March " just, production and use are all very convenient, and this has just proved that the present invention has appreciable practical prospect.
In a word, as long as each side is calculated configuration suitably, as the high explosive kind, the selection of dose, the method for the built-in time-delay percussion of cylinder, what of the cylinder number of plies, the selection of cylinder manufactured materials, determining or the like of shooting angle just can reach desirable effect.
4, description of drawings:
Accompanying drawing 1: rocket is designed to example, the schematic appearance that it is whole with three joint cylinders.
Accompanying drawing 2: the vertical section internal structure position view that is Fig. 1.
Among the figure: 1, bullet 2, preceding fin tube 3, the 3rd joint cylinder 4, the second joint cylinder
5, first segment cylinder 6, the initial boost motor 7 of conventional thrust gunpowder, back fin
8, top board (base plate of a last joint) 9, base plate (base plate of next joint) 10, cylinder circle
11, filler 12, time difference percussion lead 13 screw threads 14, screw thread
15, screw thread 16, warhead explosive 17, guidance control package
18, time difference percussion lock 19, front wing control room 20, filler
21, spherical high explosive 22, conventional thrust gunpowder 23, top board
24, base plate
5, the specific embodiment:
When the new-type thrust rocket of the present invention need be launched, light the interior conventional thrust gunpowder (2) of the initial boost motor of conventional thrust gunpowder (6) of latter end earlier rocket is delivered to the above space of 300m, the time difference percussion lock (18) of bullet bottom is sent the spark ignition by time difference percussion lead (12) then, cylinder (5) detonation takes place in the spherical high explosive (21) in first cylinder (5), detonation wave reaches the peripherad screw thread combination of trying hard to recommend between " the initial boost motor of conventional thrust gunpowder (6) " and cylinder circle (10) and upper plate (9) thereof (slippage) downwards, detonation wave is at that time axially gone up the thicker top board (9) of thrust (after certain barrel effect is strengthened) high strength promotion monoblock advances the rocket front portion, (end) plate 23 of top shown in the figure, 8,9,24 all is the shape of middle webbing book, position and its advantage of mode that they combine with cylinder circle spiral are: the combination dismounting is very convenient, can only slippage open part following and on every side behind its interior explosive detonation, and make a top board accept the huge thrust of detonation wave.At this moment after 0.1-1 after second, time difference percussion lock (18) is sent spark through time difference percussion lead (12) again and is ignited spherical high explosive (21) in second cylinder (10), top board (9) in first cylinder this moment (5) promptly is the base plate (9) of second cylinder (4), the detonation wave of same cylinder (10), separating base plate (9) and cylinder circle (10) and quickening to promote top board (8) makes rocket quicken to advance, last 0.1-1 is after second, and the 3rd cylinder (3) is ignited in time difference percussion lock (18) makes top board (23) accept the acceleration of detonation wave.In the guidance control package (17) of front portion GPS is arranged in the bullet (1), inertia, laser guidance instrument etc. make warhead explosive (16) correctly hit remote object by fin (2) before front wing control room (19) operation.
Claims (2)
1, a kind of the design of propelling force of rocket " strengthen " is characterized in that: the high explosive of circle or cylindricality is housed in modular each cylinder that can make up dismounting mutually, and the electric wire polyphone that is sent by the time difference percussion lock of bullet bottom respectively saves high explosive in the cylinder.Screw connection with screw thread between cylinder, have between the warhead and " the initial boost motor of conventional thrust gunpowder " of fin outside being combined on after each cylinder connects.
2, " strengthening the design of rocket thrust " according to claim 1 is characterized in that: the cylinder periphery is made up of the thin top board of middle webbing, base plate and tube circle, screws connection with shallow thread mutually, and there are high explosive and filler in cylinder inside.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610108813 CN101055164A (en) | 2000-12-09 | 2000-12-09 | Rocket propulsion enhancing design |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610108813 CN101055164A (en) | 2000-12-09 | 2000-12-09 | Rocket propulsion enhancing design |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB001349163A Division CN1314938C (en) | 2000-12-09 | 2000-12-09 | Propelling increasing rocket pipe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101055164A true CN101055164A (en) | 2007-10-17 |
Family
ID=38795124
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200610108813 Pending CN101055164A (en) | 2000-12-09 | 2000-12-09 | Rocket propulsion enhancing design |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101871750A (en) * | 2009-04-27 | 2010-10-27 | 施仲伟 | Design for enhancing propelling force of rocket |
| CN102826230A (en) * | 2012-08-30 | 2012-12-19 | 李继东 | Aircraft carrier gunpowder quick-propelling take-off propeller |
| CN103090745A (en) * | 2013-02-05 | 2013-05-08 | 朱旭望 | Guided missile with middle-section speed change and anti-intercept method thereof |
| CN108871110A (en) * | 2018-05-28 | 2018-11-23 | 北京航空航天大学 | Rocket and its assemble method |
| CN111121537A (en) * | 2019-12-27 | 2020-05-08 | 北京星际荣耀空间科技有限公司 | Sounding rocket system |
| CN113820095A (en) * | 2021-08-23 | 2021-12-21 | 北京强度环境研究所 | Wind tunnel scale model assembly of bundled rocket |
-
2000
- 2000-12-09 CN CN 200610108813 patent/CN101055164A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101871750A (en) * | 2009-04-27 | 2010-10-27 | 施仲伟 | Design for enhancing propelling force of rocket |
| CN102826230A (en) * | 2012-08-30 | 2012-12-19 | 李继东 | Aircraft carrier gunpowder quick-propelling take-off propeller |
| CN103090745A (en) * | 2013-02-05 | 2013-05-08 | 朱旭望 | Guided missile with middle-section speed change and anti-intercept method thereof |
| CN108871110A (en) * | 2018-05-28 | 2018-11-23 | 北京航空航天大学 | Rocket and its assemble method |
| CN111121537A (en) * | 2019-12-27 | 2020-05-08 | 北京星际荣耀空间科技有限公司 | Sounding rocket system |
| CN113820095A (en) * | 2021-08-23 | 2021-12-21 | 北京强度环境研究所 | Wind tunnel scale model assembly of bundled rocket |
| CN113820095B (en) * | 2021-08-23 | 2023-05-23 | 北京强度环境研究所 | Binding rocket wind tunnel scaling model assembly |
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Open date: 20071017 |