CN1369683A - Gravitation boosting method for launching carrier rocket - Google Patents

Abstract

A launching method of carrier rocket with gravity gyration boost is a new method for launching roacket by utilizing self-gravity of the carrier rocket to launch or help to launch rocket. The methos uses energy and motive force outside of carrier rocket to lift the rocket to certain altitude, and then to let it dive in high speed towards ground under the action of its self-gravity. The rocket will change its direction upwards to gyrate from ground and furthermor to continuous flying by utilizing its inertia or its own motive force.

Description

Gravitation boosting method for launching carrier rocket

Gravitation boosting method for launching carrier rocket is a kind of gravity that utilizes carrier rocket itself---the new rocket shooting method that the earth is launched or helped to fire a rocket the attraction of rocket, this method utilizes the energy and the power outside the carrier rocket that rocket is risen to overhead certain height earlier, make rocket fast dive earthward under self gravitation (also can with thrust own or boundary's thrust together) effect then, arriving setting height obtains to make its change direction revolution upwards fly away from ground behind the certain speed, continue flight by inertia and power own more later on, utilize this method to fire a rocket, might reduce or significantly reduce the quality of rocket itself and the consumption of propellant, reduce engine power, increase relative payload, thereby the reduction launch cost also might increase emission frequency and launching success rate.

Up to now, people fire a rocket, all be head-up with rocket, tail down, utilization is placed on the thrust of the rocket engine of rocket afterbody rocket is pushed to sky, this radiation pattern, the gravity of whole piece of rocket all becomes the load of rocket engine, the thrust of rocket engine must could be gone up to the air rocket launching greater than the gravity of rocket, since rocket engine consume a large amount of propellants---incendiary agent and oxidant need be stored in the rocket body, they have occupied the very big part in the filled vehicle mass, really the payload that need launch is relatively very little, so fire a rocket in this way, launch cost is very high.

As everyone knows, the gravity of object, be the attraction of the earth to object, also be a kind of power that makes object do accelerated motion, but its action direction is to make object move downward (falling earthward), can utilize this power that object (as rocket) is moved downward to come acceleration rocket, making it produce certain speed obtains after certain kinetic energy, make it change the sportex that built on stilts is upwards made in the direction revolution again? if can, we just can be with rocket gravity---and the load forces when firing a rocket changes " thrust " that rocket is moved upward into, meaning that we can utilize the gravity of rocket to launch or help and fire a rocket, might this tempting inference realize?

Utilizing the gravity of object to make object obtain movement velocity upwards is possible towards the direction motion of built on stilts, and people have done already like this in many occasions of daily life, below these examples people must be very familiar to:

The pendulum of pendulum clock can be put to other end eminence by an end eminence under the gravity effect;

Play on a swing, under the effect of body weight for humans power, swing is swung to other end eminence by an end eminence;

Turn off throttle during driver's descending and utilize the gravity of automobile to slide downwards, can make automobile rush to next hillside easily;

The Rollercoaster Rush of modernization in the large-scale recreation ground, the huge impulse force that produces when utilizing the gravity of roller-coaster to dive downwards can make it wind perpendicular to the helical orbit on ground several circles of revolution continuously.

More than several then examples show that it is possible utilizing the gravity of rocket to launch or help to fire a rocket, and is not wishful thinking, this patent attempts inquiring into problem that this may be significant.

Utilize the gravitation of celestial body to quicken carrier rocket and what new technology spacecraft is not, in the mankind's space flight practice, be applied already, for example:

Pioneer 10's detector of U.S.'s emission on March 2nd, 1972 has utilized the gravitation of Jupiter to fly to Saturn, and the gravitation by Saturn leaps the Pluto track again, and deep space flies to ultramundane universe;

The Cassini saturn's exploration device of U.S.'s emission on October 15th, 1997, in order to save propellant, it is around complicated Venus, and---orbital flight of Venus---earth---Jupiter, repeatedly the gravitation by these celestial bodies quickens, and then flies to Saturn.

The method of utilizing terrestrial gravitation to launch or help to fire a rocket that this patent is inquired into, though also utilize the gravitation of celestial body (earth) to quicken, but specific purposes are different with above-mentioned celestial body gravitation boosting accelerated process with principle, the specific purposes of this law are that original rocket on celestial body " is pushed away " from celestial body, use be " external force lifting rotary method "; It is the heading that utilizes the method that " elastic collision " takes place towards the gravitational field of the spacecraft of celestial body direction flight and celestial body to increase the speed of spacecraft and change it that celestial body gravitation boosting is quickened rule, but the two final purpose is identical, all is in order to reduce fuel consumption and launch cost.

The purpose of this patent is, a gravity that utilizes carrier rocket itself---the technical though that the earth is launched or helped to fire a rocket the attraction of carrier rocket is proposed, principle, benefit and specific implementation method that discussion utilizes the gravity emission of carrier rocket itself and helps to fire a rocket are for rocket scientific research and engineers and technicians and personage's reference interested.

Below we make detail in conjunction with Fig. 1～Figure 10 and describe:

Fig. 1 gravitation boosting method for launching carrier rocket fundamental diagram (one);

Fig. 2 gravitation boosting method for launching carrier rocket fundamental diagram (two);

Fig. 3 carrier rocket terrestrial gravitation ground rail revolution boosting launching site organigram;

Fig. 4 carrier rocket terrestrial gravitation subterranean tunnel revolution boosting launching site organigram;

Fig. 5 carrier rocket terrestrial gravitation submarine pipeline revolution boosting launching site organigram;

Fig. 6 carrier rocket terrestrial gravitation air-drop---subterranean tunnel revolution boosting launching site organigram;

Fig. 7 carrier rocket terrestrial gravitation vertical spin track boosting launching site organigram that circles round;

The vertical circular orbit of Fig. 8 carrier rocket terrestrial gravitation boosting launching site organigram that circles round;

The air-drop of Fig. 9 carrier rocket---aerial from turning round terrestrial gravitation boosting method for launching emission process schematic diagram;

The exceedingly high tower terrestrial gravitation of Figure 10 carrier rocket tube turning boosting launching site organigram;

The gravitation boosting method for launching carrier rocket basic functional principle as shown in Figure 1 and Figure 2, Fig. 1 is the situation of utilizing the gravity of carrier rocket own to accelerate merely; Fig. 2 is for not only to utilize the gravity of carrier rocket own but also utilize other non-gravity thrust---the situation that motor power own, boost motor thrust, railcar thrust, track thrust (such as magnetic force, compressed air thrust etc.) are accelerated, A among the figure---rocket; C---track (wherein: C₁---descending branch; C₂---meander sections; C₃---the ascent stage); D---rocket launching point (rocket vertical or be tilted to the starting point of lift-off); P_d---the rocket launching plane; H_o---rocket gravity (terrestrial gravitation) boosting drop; V_o、V _o'---the actual lift-off of rocket theory and rocket initial velocity (consider and do not consider to descend and meander sections track friction and air drag situation under the speed of rocket when beginning to go up to the air); h_f(v _o) max---initial velocity is V_oThe maximum height that rocket freely rose and reaches when the time was not considered air drag; H '_f(v _o) max---initial velocity is V_oThe actual accessible maximum height that freely rises of rocket when the time is considered air drag; h_f(v _o') max---initial velocity is V_oThe actual maximum height that freely rises and reach of rocket when ' time is not considered air drag; H '_f(v _o') max---initial velocity is v_oThe actual maximum height that freely rises and reach of rocket when ' time is considered air drag.

The employing gravitation boosting method for launching is fired a rocket, and need utilize in advance the energy and power outside the carrier rocket that rocket A is promoted to from the lift-off plane P_dOn H_oHeight, and supposition A can not or should not be herein launch with conventional launching technique, during emission, A placed C₁Starting point, then make it under self gravitation (Fig. 1) or self gravitation and other non-gravity thrust together (Fig. 2) effect along C₁Accelerated motion downwards obtains after certain speed along meander sections C₂Revolution upwards rises up in the air track ascent stage C at lift-off point d place₃Purposes have two: the together guide effect of A; One is used for reclaiming mother missile, rocket booster and Sheng carries the railcar B of rocket (supposition rocket rear class or rocket separate with these several parts at rising point d place).

Rocket theory lift-off initial velocity V_oAvailable following methods carries out approximate calculation:

If the quality of rocket A (comprising boost motor if any boost motor) is M _AThe quality of railcar B is M _BDescending branch C ₁Length be Sc ₁C ₁With the angle of vertical line be that (for the sake of simplicity, suppose track C here to α ₁Be straight line, in fact can be curve); Along C ₁The non-gravity thrust that downward direction acts on A, B is F _f(F _fCan be constance force, also can be variable force, here for the sake of simplicity, we suppose F _fBe constance force), can get

The gross mass of A, B

M＝M _A+M _B?…………………………………(1)

(work as F _fWhen not consuming the fuel on A, the B, M is a constant; Work as F _fWhen consuming the fuel on A or the B, M is a variable, and for discussing for simplicity, suppose that here M is a constant below.)

The total force of A, B

P＝Mg＝(M _A+M _B)g………………………………(2)

Wherein g is an acceleration of gravity, at the earth's surface near, desirable g=9.81 meter per second ²

P is along C ₁The component of descent direction

P '=Pcos α=(M _A+ M _B) gcos α ... (3) Sc ₁Length ${\mathrm{Sc}}_1=\frac{H_o}{\cos \mathrm{\α}}---------\left(4\right)$ Act on A, B, along C ₁The total force of downward direction

F '=P '+F _f=(M _A+ M _B) gcos α+F _f(5) by Newton's second law formula f=ma, can get $a=\frac{f}{m}-----\left(6\right)$

With f, the m in (5) formula F ', (1) formula M replacement (6) formula; With along C ₁A in acceleration a ' replacement (6) formula of downward direction A, B can get $a^{\′}=\frac{F^{\′}}{M}=\frac{(M_A+M_B)g\cos \mathrm{\α}+F_f}{M_A+M_B}$ $=g\cos \mathrm{\α}+\frac{F_f}{M_A+M_B}------\left(7\right)$ By uniformly accelerated motion speed and distance formula

V＝at…………………………………(8) $S=\frac{1}{2}{\mathrm{at}}^2------\left(9\right)$ Can get $V=\sqrt{2\mathrm{as}}------\left(10\right)$

With (7) formula a ', (4) formula Sc ₁Replace a, s in (10) formula, can get A, B moves to Sc ₁End speed when terminal ${\mathrm{Vsc}}_1=\sqrt{2a^{\′}{\mathrm{Sc}}_1}$ $=\sqrt{2(g\cos \mathrm{\α}+\frac{F_f}{M_A+M_B})\frac{H_o}{\cos \mathrm{\α}}}$ $=\sqrt{2(g+\frac{F_f}{(M_A+M_B)\cos \mathrm{\α}})H_o}--------\left(11\right)$ Order $a_f\↓=\frac{F_f}{(M_A+M_B)\cos \mathrm{\α}}------\left(12\right)$

Be non-gravity thrust F _fThe A that causes, B equivalence be acceleration vertically downward, and substitution (11) formula has ${\mathrm{Vsc}}_1=\sqrt{2(g+a_f\↓)H_o}------\left(13\right)$ Order

A ↓=g+a _f↓ ... (14) be A, B equivalence total acceleration vertically downward, substitution (13) formula has ${\mathrm{Vsc}}_1=\sqrt{2a\↓H_o}------\left(15\right)$ To Fig. 1 situation, because of no non-gravity thrust in A, B, F _f=0, a is arranged _f↓=0, a ↓=g, so have ${\mathrm{Vsc}}_1=\sqrt{2g{H}_o}------\left(16\right)$

(16), (15) two formulas, promptly under two kinds of situations of Fig. 1, Fig. 2, do not consider track C ₁Under frictional resistance and the air drag situation, A, B move to track descending branch C ₁Speed when terminal.Because meander sections C ₂Only change the velocity attitude of A, B, do not change the numerical value of speed, so do not considering C ₂Under the situation of the speed loss that causes, can think the theory lift-off initial velocity V of rocket A on the numerical value _o=Vsc ₁, that is,, have Fig. 1 $V_o=\sqrt{2g{H}_o}------\left(17\right)$ To Fig. 2, have $V_o=\sqrt{2a\↓H_o}------\left(18\right)$

Formula (17), (18) are not considered at track meander sections C ₂Exist non-gravity thrust to quicken situation (at the decline and the rising part of meander sections, because of gravity quickens and the gravity deceleration can be cancelled out each other, so can not consider.), if at meander sections C ₂Also utilize non-gravity thrust to quicken, the lift-off initial velocity V of rocket A _oObviously will be greater than the calculated value of (17), (18) two formulas, computational methods are not discussed here, but need take into account during actual design.

Make (14) formula equivalence total acceleration vertically downward

A ↓=g+a _f↓=β g ... (19) wherein $\mathrm{\β}=1+\frac{a_f\↓}{g}------\left(20\right)$ Be the acceleration of gravity multiple.

With (19) formula substitution (18) formula, get V _oGeneral type table one V _o～H _o, β corresponding relation tables of data $V_o=\sqrt{2\mathrm{\βg}{H}_o}-------\left(21\right)$

As β=1, (promptly not having the non-gravity thrust when A, B), (21) formula promptly is converted into (17) formula.

Table one is listed V _oWith H _oAnd some the corresponding relation data between the β (=1～5), for design reference.

Make rocket A lift-off point d place and its first order or with its boost motor or with contain the railcar B that carries it and separate, A is just with initial velocity V at this moment _oMove upward, if the air drag when not considering that A moves upward, the A accessible maximum height that freely rises was h when the A engine misfired _f(v _o) max, h _f(v _o) value of max can be by the uniformly retarded motion speed formula

V=V _o-gt ... (22) and the distance formula $h=V_{o}t-\frac{1}{2}{\mathrm{gt}}^2-------\left(23\right)$ Try to achieve:

A rises to maximum height h _f=h _f(v _o) during max, V=0 is by (22) Shi Kede $t_{V=0}=\frac{V_o}{g}$ Substitution (23) Shi Kede $h\left(v_o\right)\max =V_o\frac{V_o}{g}-\frac{1}{2}g\frac{V_o^2}{g}=\frac{V_o^2}{2g}-----\left(24\right)$

By (21) formula As can be known, to Fig. 1 situation, because of β=1, substitution (24) formula has

h _f(v _o) max=H _oTo Fig. 2, because of β＞1, substitution (24) formula has

h _f(v _o) max=β H _o＞H _oβ is bigger, h _f(v _o) max compares H _oThe more big.

Table two is listed h _f(v _o) max and V _oBetween some corresponding relation data, for design reference.

Because air drag is an objective reality, so the actual accessible maximum height that freely rises of A

h′ _f(v _o)max＜h _f(v _o)max

H ' _f(v _o) max compares h _f(v _o) max less what, depend on the speed of aerodynamic performance and the A of rocket A.

As A along C ₁, C ₂When decline and revolution, the speed loss that track friction and air drag cause can not be ignored, and then A is at the actual lift-off initial velocity V at lift-off point d place _o'＜V _o, in Fig. 1, Fig. 2, use h respectively _f(v _o') max and h ' _f(v _o') max represents the A theoretical maximum height and the actual maximum height that can freely rise and reach this moment, obviously have

h _f(v _o') max＜h _f(v _o) max and

h′ _f(v _o′)max＜h′ _f(v _o)max

Below we estimate roughly, adopt the gravitation boosting method to compare with adopting traditional Vertical Launch method, what can the rocket quality reduce? what can payload increase relatively?

In order to compare, we have two pieces of rocket A ' and A at hypothesis ", the former is with vertical table two h _f(v _o) max～V _oThe corresponding relation tables of data

???V o(meter per second)	h f(v o) max(rice)	???V o(meter per second)	h f(v o) max(rice)	??V o(meter per second)	?h f(v o) max(rice)
						????30	??46	??290	??4286	????600	????18349
????40	??82	??300	??4587	????620	????19592
						????50	??127	??310	??4898	????640	????20977
????60	??184	??320	??5219	????660	????22202
						????70	??250	??330	??5551	????680	????23568
????80	??326	??340	??5892	????700	????24975
						????90	??413	??350	??6244	????720	????26422
????100	??510	??360	??6606	????740	????27910
						????110	??617	??370	??6978	????760	????29439
????120	??734	??380	??7360	????780	????31009
						????130	??861	??390	??7752	????800	????32620
????140	??999	??400	??8155	????820	????34271
						????150	??1147	??410	??8568	????840	????35963
????160	??1305	??420	??8991	????860	????37696
						????170	??1473	??430	??9424	????880	????39470
????180	??1651	??440	??9868	????900	????41284
						????190	??1840	??450	??10321	????920	????43140
????200	??2039	??460	??10785	????940	????45036
						????210	??2248	??470	??11259	????960	????46972
????220	??2467	??480	??11743	????980	????48950
						????230	??2696	??490	??12238	???1000	????50968
????240	??2936	??500	??12742	???1200	????73395
						????250	??3186	??520	??13782	???1400	????99898
????260	??3445	??540	??14862	???1600	????130479
						????270	??3716	??560	??15984	???1800	????165138
????280	??3996	??580	??17146	???2000	????203874

Shooting method, the latter launch with gravitation boosting method for launching, and the two initial mass is respectively m _o' and m _o"; The two instantaneous mass is m ' and m "; M identical in quality during the two engine misses _n'=m _n"=m _n(quality when we are with engine misses here is considered as the effective mass of rocket); The identical Vn ' of end speed=Vn "=Vn; The also identical C ' of the jet velocity of rocket engine=C "=C; The takeoff speed of A ' is 0, A " takeoff speed be V _o

Calculate for simplifying, we suppose A ＇, A " back that lifts off is along the orbital flight perpendicular to ground, and the flight time is respectively t ＇, t ".

End speed Vn ', Vn when rocket engine is flame-out " can be by existing the neat AudioCodes Paderewski formula under gravitational field and the air drag situation to calculate: ${\mathrm{Vn}}^{\′}=\mathrm{Vn}=\mathrm{CIn}\frac{m_o^{\′}}{m_n}-{\mathrm{gt}}^{\′}{\∫}_o^{t^{\′}}\frac{D^{\′}}{m^{\′}}\mathrm{dt}--------\left(25\right)$ ${\mathrm{Vn}}^{\′\′}=\mathrm{Vn}=\mathrm{CIn}\frac{m_o^{\′\′}}{m_n}-{\mathrm{gt}}^{\′\′}{\∫}_o^{t^{\′\′}}\frac{D^{\′\′}}{m^{\′\′}}\mathrm{dt}+V_o-------\left(26\right)$

(25), first on equal sign the right is the characteristic velocity of calculating by neat AudioCodes Paderewski formula under the ideal case in (26) formula; Second speed loss that causes for the gravity loss; The 3rd is air drag D ', the D " speed loss that causes; The 4th is A " initial velocity.

" difference is not very big, calculates for simplifying, and we suppose that the gravity consume speed loss that loss causes with air drag of two pieces of rockets is approximate identical, promptly has for because A ', A ${\mathrm{gt}}^{\′}+{\∫}_o^{t^{\′}}\frac{D^{\′}}{m^{\′}}\mathrm{dt}\≈g{t}^{\′\′}+{\∫}_o^{t^{\′\′}}\frac{D^{\′\′}}{m^{\′\′}}\mathrm{dt}$ We make ${\mathrm{gt}}^{\′}+{\∫}_o^{t^{\′}}\frac{D^{\′}}{m^{\′}}\mathrm{dt}=g{t}^{\′\′}+{\∫}_o^{t^{\′\′}}\frac{D^{\′\′}}{m^{\′\′}}\mathrm{dt}=K---\left(27\right)$

(because A ", quality is less than the quality of A ', A " movement velocity greater than A ', t is arranged "＜t ', and this simplification causes result of calculation partially bad, actual effect can be more better)

(27) substitution (25), (26) can get $\frac{m_o^{\′}}{m_n}=e^{\frac{V_n+K}{c}}------------\left(28\right)$ $\frac{m_o^{\′\′}}{m_n}=e^{\frac{V_n+K-V_o}{c}}-------\left(29\right)$ (28) substitution (29) can get $\frac{m_o^{\′\′}}{m_n}=\frac{m_o^{\′}}{m_n}{e}^{-\frac{V_o}{c}}--------\left(30\right)$ Can get A thus ", A ' initial mass ratio $\frac{m_o^{\′\′}}{m_o^{\′}}=e^{-\frac{V_o}{c}}-----\left(31\right)$

Rocket A ', A " relative payload N ', N " are respectively A ', A " payload m _n'=m _n, m _n"=m _nWith their initial mass m _o', m _o" ratio, so can get A by (30) formula ", A ' be payload ratio relatively $\frac{N^{\′\′}}{N^{\′}}=e^{\frac{V_o}{c}}-----\left(32\right)$

Some A that calculate by (31), (32) two formulas ", A ' mass ratio

With relative payload ratio With

The corresponding relation data be shown in table three.

By (31), (32) two formulas and table three as can be known, V _oBigger, Bigger, emission table three

The corresponding relation tables of data When identical payload obtains identical speed, A " initial mass the more littler than A ', payload ratio A ' increases the more relatively.For example, during jet velocity C=3000 meter per second, V _oDuring=300,900,1500,1800,2100 meter per seconds,

Be respectively 0.1,0.3,0.5,0.6,0.7, suppose that A ' initial mass is 10 tons, A " initial mass can reduce to 9.1,7.4,6.1,5.5,5.0 tons respectively; Payload can increase to 1.11,1.35,1.65,1.73,2.01 times respectively relatively.

Can with less propellant identical payload be launched with more small-sized rocket, this is the advantage and the main economic benefit place of gravitation boosting method for launching carrier rocket.

Though adopt carrier rocket gravitation boosting method to fire a rocket still to need consumes energy that rocket A (lighter A " and prime or boost motor, railcar etc., rather than heavier A ') is promoted to from lift-off plane H _oEminence, produces non-gravity thrust and also want consumes energy, but that at this moment consume is A " outside the energy, and can be the general common energy, as gasoline, diesel oil, electric power, manpower, animal power etc., price is than propellant considerably cheaper, also safety many.

Below we introduce the specific implementation method of several gravitation boosting method for launching carrier rocket.

Figure 3 shows that carrier rocket terrestrial gravitation ground rail revolution boosting launching site organigram, track C can be close to the high mountain hillside and build L ₁, L ₂Be ground and rocket assembly and adjustment workshop, mountain top; T is the elevator that transports rocket (or rocket part) and wait (also lifting facilities and equipment such as highway, helicopter), the rocket A and the track way of contact can be slidingtype, roller and floated, rocket A also can be placed on the railcar B, for A and B can be turned round smoothly, meander sections need have the enough big radius of gyration.Because tellurian high mountain, what height above sea level was the highest is the Mountain Everest in 8848.13 meters the Himalayas, therefore the H at this launching site _oValue can not be worth (the H that reality can reach greater than this _oBe worth more much smaller than this value), for increase H as far as possible _oShould be chosen in from the face of land (foot of the hill) during the value addressing has other construction of high mountain of big drop;

Figure 4 shows that carrier rocket terrestrial gravitation subterranean tunnel revolution boosting launching site organigram, because high mountain is limited from the height on the face of land, for increasing H _o, can adopt method to underground extension, build subterranean tunnel formula launching site, also can build the launching site of this form as needs when hidden, track C is placed in the tunnel O, need build vertical service aisle E for ease of work ₁, E ₂With horizontal service aisle G.There is a very big advantage at the tunnel type launching site, can vacuumize, therefore can significantly reduce A, the B air drag when in the tunnel, moving, the energy consumption that vacuumizes for minimizing, can be provided with at the import and export of tunnel O can fast automatic opening and closing shutter the sealing transition section, at this moment needn't launch at every turn full tunnel is vacuumized again, only need head, tail two changeover portions are vacuumized;

Figure 5 shows that carrier rocket terrestrial gravitation submarine pipeline revolution boosting launching site organigram,, also can adopt the method that pipeline O is sunk under the water to build the launching site for avoiding excavating the difficulty in tunnel.The degree of depth of earth ocean generally between tens meters～several kms, the darkest Pacific Ocean Ma Liyana trench, the depth of water reaches 10916 meters, as seen, adopts the submarine pipeline method to build the launching site, increases H _oVery big potentiality are arranged, need overcome huge hydraulic pressure but build the submarine pipeline launching site, the every increase of the depth of water is 10 meters under the sea level, hydraulic pressure increases an atmospheric pressure, during depth of water 5000m, hydraulic pressure can reach 500 atmospheric pressure, and the deep water section of pipeline O, service aisle E, G must sustain the hydraulic pressure at this place.

In order further to increase H _o, also Fig. 3,4,5 launching sites can be connected in series, at this moment H _oMight reach 5000～ten thousand metres;

Figure 6 shows that the air-drop of carrier rocket terrestrial gravitation---subterranean tunnel revolution boosting launching site organigram, this launching site adopts another kind of way to increase H _oIt utilizes lifting instruments such as dirigible, balloon, aircraft that A is promoted to overhead very high height (if A can not or should not directly launch) earlier on this height, aiming at a following infundibulate receiver I who excavates at the high mountain middle part then abandons A, A slips into underground revolution tunnel O along the I wall after falling into I, and ground at last flies out from the exit of tunnel O.The advantage of this method is H _oCan be high more a lot of than the height h of ground high mountain, therefore might obtain very big lift-off initial velocity V _o, for example, rocket A is promoted to overhead 20～30 kilometers places and abandons (this is possible), during decline as quickening (β=1), the lift-off initial velocity V after the revolution with gravity merely _o626～767 meter per seconds (seeing Table one) can be reached,, then bigger V can be obtained as when falling and in tunnel O, carry out non-gravity again and quicken _oValue.

The major technique difficulty of air-drop method is, how to guarantee that A can fall into the I neutralization and how prevent from not damaged when the A that falls at a high speed from contact with the I wall, and the former utilizes the solution of being not difficult of advanced person's electronic navigation location technology; The latter should make the ratio of the high h in bell mouth diameter phi and mountain as far as possible little and adopt the crashproof material of high-quality to cover hopper walls, certainly the structural strength that increases A also is a way, optimal way is, set up a high-intensity magnetic field cover layer on the I wall and in tunnel O, setting up the last one shifting magnetic field, A is not directly contacted with I, O wall, suspending and passing through I, O, and under the effect of the shifting magnetic field of O, further quickening.

Though the air-drop method is a kind of increase H _oFairly simple method, but bigger danger is arranged, rocket is abandon from the high-altitude, just as one piece of cookle very unexpectedly, consequence is very serious just in case accidentally drop, therefore need to adopt the various effective and safe precautionary measures, should be as the launching site away from residential block (at sea building on the isolated island), when falling, rocket answers its track of tracking measurement, depart from bell mouth as finding, then should make its automatic or its deceleration that releases a parachute of remote control, safe falling ground or sea, as have little time to release a parachute, can aloft it be ignited;

Fig. 7, Figure 8 shows that carrier rocket terrestrial gravitation vertical spin track and the vertical circular orbit boosting launching site organigram that circles round, the launching site of these two kinds of forms adopts another kind of way to increase H _o, promptly repeatedly recycling the sustained height drop---the diameter phi of spiral and circular orbit repeatedly utilizes the earth that the gravitation of carrier rocket is quickened carrier rocket, the equivalent H at these two kinds of launching sites _o' be

H _o'=n φ ... (33) n wherein to helical orbit, is the spiral number of turns; To circular orbit, be the rocket number of turns of circling round.

The difference of Fig. 7 and Fig. 8 is that the number of turns n of Fig. 7 spiral is fewer to be fixed value, so H _oThe value that increases is not very big, but track construction is simpler; The number of turns n that circles round of Fig. 8 circular orbit can be very big, and unrestricted in theory, so H _oValue added can be very big, but track construction is complicated, the place, gateway need be provided with the fast railway conversion equipment.Vertical circumference shown in Figure 8 circle round track textural some be similar to large-scale high-energy physics experiment device particle cyclotron, main difference is that latter's orbit plane is parallel to the ground; The former orbit plane is perpendicular to the ground.

Quicken the rocket A that moves for the terrestrial gravitation that repeatedly reuses same drop φ in spiral and circular orbit, Fig. 7, Fig. 8 emission system need satisfy a primary condition, promptly rise half-turn Y in orbit _i", track needs to provide the thrust that equals A gravity at least to A, to offset A along rising half-turn Y _i" speed loss that the gravity of A causes during operation, like this, A moves to track peak X ₁The time just can keep it along track descending branch Y _i" fall to minimum point X ₂The time linear velocity Vx that obtained ₂I promptly has

Vx _{1 (i+1)}=Vx ₂I ... (34) Vx in (34) formula ₁(i+1) be the starting velocity of next circle of A, i.e. i+1 circle descending branch Y _I+1' initial velocity.

Below we come the lift-off initial velocity V that leaves the right or normal track of calculating chart 7, Fig. 8 A _o

For simplicity, we discuss first, rise half-turn Y in orbit _i" speed increment that thrust produced that provides by track just in time with A this half-turn because of the speed loss that gravity causes offset (this supposes in fact not need to do so only for convenience of calculation), at track decline half-turn Y _i' no non-gravity acts on this situation of A, and at this moment (34) formula is set up, track ascent stage Y _i" effect can ignore, can be considered and not exist.

Below we discuss the energy variation situation of A at (i+1) circle decline half-turn, the speed loss that air drag when suppose A decline and track friction resistance cause can be ignored, then A drops to X ₂Kinetic energy during point $E{x}_2=\frac{1}{2}{m}_A{V}_{X_2(i+1)}^2-------\left(35\right)$ Should equal A at X ₁Kinetic energy during point $E_{X_1}=\frac{1}{2}{m}_A{V}_{X_1(i+1)}^2=\frac{1}{2}{m}_A{V}_{X_{2}i}^2------\left(36\right)$ With A by X ₁Point drops down onto X ₂The point terrestrial gravitation is to merit (being the minimizing value of A potential energy) that A did

W _φ=m _Ag _φ(37) sum of the two promptly has $E_{X_2}=E_{X_1}+W_{\mathrm{\φ}}------\left(38\right)$ With (35), (36), (37) formula substitution (38) formula, have $\frac{1}{2}{m}_A{V}_{X_2(i+1)}^2=\frac{1}{2}{m_A{V}_{X_{2}i}^2+m}_A\mathrm{g\φ}$ Can get thus $V_{X_2(i+1)}^2=V_{X_{2}i}^2+2\mathrm{g\φ}--------\left(39\right)$ At the n circle, promptly the last circle has $V_{X_{2}n}^2=V_{X_2(n-1)}^2+2\mathrm{g\φ}$ $=V_{X_2(n-2)}^2+2\mathrm{g\φ}+2\mathrm{g\φ}$ $=V_{X_2(n-3)}^2+2\mathrm{g\φ}+2g\mathrm{\φ}+2\mathrm{g\φ}$ =...=n2g φ ... (40) promptly have $V_{x_{2}n}=\sqrt{2\mathrm{gn\φ}}-----\left(41\right)$

Rocket A leaves the lift-off initial velocity V of vertical spin and vertical circular orbit _oEqual A on the numerical value at n circle minimum point X ₂The speed at place

, promptly have $V_o=V_{x_{2}n}=\sqrt{2\mathrm{gn\φ}}------\left(42\right)$ Table four is listed V _oAnd some corresponding relation data between n, the φ are for design reference.Contrast (42) and (17) formula, order

H _o'=n φ ... (43) be the terrestrial gravitation equivalence boosting drop of vertical spin and vertical circular orbit, as can be known, n the more, H _o' value is bigger.(43) formula substitution (42) formula can get $V_o=\sqrt{2g{H}_o^{\′}}------\left(44\right)$ In non-gravity thrust greater than rocket gravity and impose on (this table four V under the situation of rocket A continuously _o～n, φ corresponding relation tables of data

The time non-gravity thrust can be not limited to track thrust, also can be the thrust of thrust, boost motor and the railcar of the rocket first order, but provide the effect of thrust best with track), at the decline half-turn Y of track _i', A utilize gravity and non-gravity make a concerted effort quicken; Rising half-turn Y at track _i", A utilizes the difference of non-gravity and gravity to quicken, at this moment, and the lift-off initial velocity V that leaves the right or normal track of rocket A _oWill greater than or much larger than the calculated value of (43) formula.

Table four is a theoretical value, in fact will obtain very big V _oValue is very difficult, when especially the quality of rocket A is very big, reason is the quality that the quality of rocket A is far longer than elementary particle, the order of magnitude is between tens kilograms to tens tons, the centrifugal force that it produces when circular orbit moves is very big, the structure of rail system must be very firm, otherwise speed is increased to a certain degree, whole system will be disintegrated, though this belongs to the problem of engineering-built technology aspect, because of being related to this emission system, it can build success, thus emphasized especially here, to attract much attention.Obviously, this emission system is used for launching miniature proper with pencil rocket, and technical difficulty is lower, builds than being easier to.

Vertical spin not necessarily is built on the ground with vertical circular orbit launching site, also can build massif inside or underground in, or part is built on the ground, part is built underground in, track also can place in the pipeline, be to reduce air drag, also vacuum-pumping in the pipeline.Non-gravity thrust preferably adopts track or pipeline thrust (as magnetic force), as adopt the rocket first order, boost motor and railcar thrust, owing in earth atmosphere, move fully, engine on the rocket first order, boost motor and the railcar can use air breathing jet engine, only need to consume the cheap fuel such as gasoline of price comparison, propellant that needn't consume expensive;

Figure 9 shows that the carrier rocket air-drop---aerial from turning round terrestrial gravitation boosting method for launching emission process schematic diagram.This method is different with above several methods, and it utilizes the power of carrier rocket itself to realize revolution aloft voluntarily.Build track, tunnel, duct type launching site, engineering is very great, and technology is quite complicated, invest very greatly, if we can make rocket realize turning round, just can avoid building the launching site, saves a large sum of engineering cost aloft.May carrier rocket has or not realize revolution aloft voluntarily? it is possible utilizing the powerful thrust of rocket engine.We know, the aviation aerobat that some is skilled in technique can make aircraft vertically or almost fast dive earthward vertically, and during soon near ground, the pull-up head makes the aircraft revolution upwards rapidly, soars up to the sky with as powerful as a thunderbolt gesture.The carrier rocket air-drop---aerial acrobatic maneuver is similar therewith from turning round emission process, and the means of transport that its first utilization can be flown in earth dense atmosphere (as balloon, aircraft, dirigible) etc. is promoted to overhead H with carrier rocket A _d+ H _oHeight (H _dBe the lift-off plane P _dHeight overhead), makes A fast dive earthward under terrestrial gravitation (also can with motor power own or boost motor thrust together) effect then, arrive overhead H _dHeight the time, change the jet direction of engine, make the A revolution upwards, and vertically or obliquely fly away from ground at a lift-off point d place, the lift when upwards turning round for utilizing air dynamic behaviour to increase A, A can be with and fix or telescopic flank;

Figure 10 shows that the exceedingly high tower terrestrial gravitation of carrier rocket tube turning boosting launching site organigram, this is a kind of rocket launching site for following human design, if can build highly high " exceedingly high tower " (this paper does not discuss the method for construction of exceedingly high tower) of passing through earth dense atmosphere of success human future, fire a rocket just we can utilize the huge tower height drop (as 10～100 kilometers) of exceedingly high tower to launch or help.

As everyone knows, with rocket move to from ground high-altitude (as exceedingly high cat head) go the emission also might be than saving a lot of propellants in the ground surface launching, if but we utilize the exceedingly high tower of Figure 10 (a)～(d) form, use gravitation boosting method β in season＞1, then might than at cat head with legacy transmission method saving more propellant, when β=1, when promptly utilizing terrestrial gravitation to quicken merely, the two effect of saving propellant in theory is identical, and, if there is air drag, the gravitation boosting method is good not as good as the direct shooting method of cat head, this point is understood that, the speed that obtains merely at the bottom of gravity effect tenesmus drops down onto tower the time because of rocket, when not having air drag, the speed loss that causes because of gravity when just in time rising to cat head with it at the bottom of the tower is cancelled out each other, when having air drag, speed loss that causes because of gravity when the speed that obtains when dropping down onto at the bottom of the tower rises to cat head less than it and the speed loss sum of the two that causes because of air drag; If but β＞1, be that A when falling (revolution and when rising also can) not only utilizes terrestrial gravitation to quicken, also utilize other non-gravity thrust to quicken, as motor power own, boost motor thrust, especially the thrust that provides of track and pipeline is quickened, then the gravitation boosting method benefit of saving propellant just might be than much better during with direct shooting method at cat head, and table one data can illustrate this point.

Figure 10 (a)～(c) is tower launching site, single-pass sky; (d) be tower launching site, bilateral sky, (a) a vertical pipe O is arranged in the type tower, rocket A works in self gravitation and other non-gravity thrust one along O (or along the track C that places in the O) and constantly quickens down to weigh down earthward, after underground meander sections is turned round, launches from floor outlet; (b) a vertical pipe O is arranged in the type tower, different with (a), A returns this O rising once more after it falls revolution, go up to the air from cat head at last; (c) two vertical pipes are arranged in the type tower, A is fallen by a pipe and is risen by another pipe after underground meander sections revolution, is gone up to the air by cat head at last; (d) the every tower of type all has a vertical pipe, and A is descended by a tower vertical pipe and risen column overhead lift-off thus at last by another tower vertical pipe after underground meander sections revolution.Be the minimizing air drag, equal vacuum-pumping in O pipe and the meander sections pipeline also can be set up high-intensity magnetic field or mobile high-intensity magnetic field on O pipe and return bend tube wall, A is being suspended move therein.

When vertical pipe O in building exceedingly high tower and track C, there is a problem to arouse attention, because exceedingly high tower is very high, cat head can not be ignored with the different of tower bottom line speed during earth rotation, the different tracks that can cause A to fall and rise of cat head and tower bottom line speed are not exclusively perpendicular to ground, so between O, C and the vertical line a little inclination angle should be arranged, size is relevant with the geographic latitude of tower height and tower, also relevant the running time in O with A.

From above introduction as can be known, when if we fire a rocket, change traditional way, its direction is reversed, allow it upside down, tail up, utilize the gravity of itself earlier, promptly the earth makes it obtain a lift-off initial velocity to its attraction and other non-gravity thrust, we just might be to a certain extent or reduce the quality of rocket itself and the consumption of propellant largely, reach the purpose that reduces launch cost.

Though the operation principle of gravitation boosting method for launching carrier rocket is very simple, it is so uneasy to implement, especially H _oThe launching site very big with φ, project scale is very big, reliability requirement is high, because rocket dives downwards from eminence, impulse force is very big, speed is exceedingly fast, and very big danger is arranged, especially β＞1, open the throttle again when being equivalent to automobile downhill, the driver does seldom like this, but considers that the downward acceleration rocket of identical thrust can make rocket obtain to many acceleration of 2g than acceleration rocket upwards, therefore in order to increase the lift-off initial velocity of rocket as far as possible, improve this law benefit, make β＞1st when needing, be necessary, in order to reduce launch cost by a relatively large margin, this danger is worth emitting.

For the purpose of prudent, the interesting implementer of suggestion carries out H earlier _oWith the not too big miniature and bench model rocket launching of φ test, mould rope rule, accumulate experience, heighten one's confidence, increase H again after the initial success _o, φ and rocket diameter, fully success and confirm to have big benefit after carries out formal rocket launching test again, arrange possibility proper like this.

Claims (1)

1. novel gravitation boosting method for launching carrier rocket is characterized in that:

When a. adopting this method to fire a rocket, utilize the energy and power outside the carrier rocket that rocket is risen to overhead certain height earlier, make rocket work fast dive earthward then at self gravitation (earth is to the attraction of rocket) or with other non-gravity thrust one, arrive setting height and obtain to make its change direction revolution upwards fly away from ground behind the certain speed, continue flight by inertia and power own more later on;

B. gravitation boosting method for launching carrier rocket can have following several concrete form of implementation: ground rail revolution boosting launching site; Subterranean tunnel revolution boosting launching site; Submarine pipeline revolution boosting launching site; Air-drop---subterranean tunnel revolution boosting launching site; Air-drop---aerial from turning round the terrestrial gravitation boosting method for launching; Exceedingly high tower tube turning boosting launching site; Vertical spin track and the vertical circular orbit boosting launching site etc. of circling round, in order to increase rocket gravity (terrestrial gravitation) boosting drop H, multi-form launching site can be connected in series use;

C. aerial rocket gravity (terrestrial gravitation) the boosting drop H of ground rail, subterranean tunnel, submarine pipeline, air-drop---subterranean tunnel, air-drop---from revolution and exceedingly high tower tube turning boosting launching site _oFor rocket is raised a little to rocket lift-off plane P _dVertical range, rocket A is at the lift-off initial velocity of lift-off point d place acquisition $V_o=\sqrt{2a\↓H_o}=\sqrt{2\mathrm{\βg}{H}_o}-----------\left(21\right)$ Wherein a ↓=g+a _f↓=β g (19) is the equivalence total acceleration vertically downward of rocket A and railcar B $a{f}_{}\↓=\frac{F_f}{(M_A+M_B)\cos \mathrm{\α}}-----\left(12\right)$ Be non-gravity thrust F _fThe A that causes, B equivalence be acceleration (M wherein vertically downward _A, M _BQuality for A, B; α is F _fAnd the angle between the vertical line); $\mathrm{\β}=1+\frac{a_f\↓}{g}-----\left(20\right)$ Be the acceleration of gravity multiple; The g=9.81 meter per second ²---acceleration of gravity.

As the non-gravity thrust also being arranged in A, B in meander sections, then the lift-off initial velocity of A will be greater than (21) formula calculated value;

D. vertical spin and vertical circular orbit equivalent rocket gravity (terrestrial gravitation) the boosting drop at boosting launching site that circles round

H _o'=n φ ... (33) wherein φ is the diameter of helical orbit and circular orbit; N to helical orbit, is the spiral number of turns; To circular orbit, be the rocket number of turns of circling round.

Vertical spin need satisfy a primary condition when circling round the work of boosting emission system with vertical circular orbit terrestrial gravitation: rise half-turn in orbit, track needs to provide the thrust that equals A gravity at least to rocket A, to offset the A speed loss that the gravity of A causes when the rising half-turn moves, just in time can offset under the situation of the speed loss that rocket gravity causes the circle round lift-off initial velocity that leaves the right or normal track of boosting emission system rocket A of vertical spin and vertical circular orbit terrestrial gravitation at the speed increment that thrust that track provides produces $V_o=\sqrt{2\mathrm{gn\φ}}-------\left(42\right)$ $=\sqrt{2g{H}_o^{\′}}-------\left(44\right)$

Rise speed increment that half-turn produces to non-gravity thrust (being not limited to the thrust of track) that rocket provides in orbit and act under the situation of A the lift-off initial velocity V that leaves the right or normal track of rocket A constantly greater than speed loss and the non-gravity thrust that the gravity of rocket A causes _oWill be greater than (42), (44) formula calculated value;

E. to bestow the non-gravity thrust of rocket A can be rocket first order motor power, booster thrust, railcar thrust, track thrust (as magnetic force, compressed air thrust etc.) to carrier rocket gravitation boosting emission system, be in fully in the earth dense atmosphere as emission system, the engine that uses when A descends, turns round and circles round can be common air breathing jet engine, only need to consume the cheap fuel such as gasoline of price comparison, needn't use rocket engine, the propellant of consume expensive;

F. carrier rocket A and contain to carry its railcar B and the way of contact between the track of gravitation boosting emission system, pipeline, tunnel, can be slidingtype, roller and floated, move in pipeline and tunnel as A, B, air drag when moving for reducing can be evacuated pipeline, tunnel internal.

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