CN112896563A - Pulley block type rocket launching method and device - Google Patents

Pulley block type rocket launching method and device Download PDF

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CN112896563A
CN112896563A CN202110222501.4A CN202110222501A CN112896563A CN 112896563 A CN112896563 A CN 112896563A CN 202110222501 A CN202110222501 A CN 202110222501A CN 112896563 A CN112896563 A CN 112896563A
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rope
pulley block
carrier rocket
weight
rocket
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曹瑞
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets

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Abstract

The embodiment of the invention discloses a pulley block type rocket catapult launching method and a pulley block type rocket catapult launching device, which comprise rope traction, movable pulley block distribution, auxiliary force source configuration, data simulation, data substitution and the like, and are provided with a device composed of a launching frame, a rope, a movable pulley block, a weight and the like, wherein the carrier rocket is accelerated to move through the self weight of the weight, and after the carrier rocket reaches an initial speed value, the rope on the carrier rocket is released and is ignited to launch. The invention pre-accelerates the carrier rocket to a certain initial speed before the rocket is ignited by a traction mode so as to save the rocket fuel and further promote the effective load of the rocket.

Description

Pulley block type rocket launching method and device
Technical Field
The embodiment of the invention relates to the technical field of aerospace, in particular to a pulley block type rocket ejection launching method and device.
Background
The existing rocket launching modes mainly comprise compressed air launching, gas launching, steam launching, boosting rocket launching, electromagnetic launching and the like. Because of the huge mass of the carrier rocket, only one boosting rocket is used in the ejection mode at present. Electromagnetic ejection is still in the technical development stage at present as a feasible technical scheme.
The ejection mode of the boosting rocket has performance limit, and the lifting of the carrying capacity of the carrier rocket is limited. The electromagnetic launching technology of the carrier rocket cannot enter a practical stage temporarily due to the power limitation of electrical equipment and the like at present.
Disclosure of Invention
Therefore, the embodiment of the invention provides a pulley set type rocket launching method and device, and aims to solve the problem that the launching mode of a boosting rocket in the prior art is low in lifting the transport capacity of a carrier rocket.
In order to achieve the above object, the embodiments of the present invention provide the following technical solutions:
according to a first aspect of the embodiments of the present invention, a pulley block type rocket launching method is characterized in that the pulley block type rocket launching method includes the following steps:
s1, adopting a rope for traction, arranging a movable pulley block on one side of a launcher of the carrier rocket, fixing one end of the rope on the carrier rocket through a connecting device capable of controlling separation, and connecting the other end of the rope with a heavy object through the movable pulley block;
s2, distributing a plurality of movable pulleys contained in the movable pulley block, dividing the movable pulley block into an upper pulley block and a lower pulley block which are oppositely arranged in the vertical direction, sequentially winding one end, far away from the carrier rocket, of a rope on the movable pulleys of the movable pulley block in an outward-inward winding mode, setting the number of the movable pulleys of the movable pulley block to be N, setting the number of the windings to be N, and taking N to be N + 1;
s3, providing a power assisting source, wherein the power assisting source comprises the steps that a weight is arranged below a movable pulley block, the weight is connected to the bottom end of a lower pulley block, the weight is driven by the weight to drive a rope to pull a carrier rocket to pre-accelerate in the vertical upward direction, the mass of the weight is M, and the mass of the carrier rocket is M;
s4, simulating data, including setting the moving distance of the carrier rocket as S1Time of exercise t1At a speed v of movement1Acceleration of motion of a1；
And the movement distance of the weight is S2Time of exercise t2At a speed v of movement2Acceleration of motion of a2；
And (3) analyzing and obtaining the following stress under the condition of neglecting the gravity and the friction force of the rope and the pulley: t is t1＝t2，S1＝NS2，v1＝Nv2，a1＝Na2；
Figure BDA0002954736680000021
Based additionally on the velocity-displacement formula v2Available as 2 as:
thus, it follows:
Figure BDA0002954736680000022
further derive the acceleration formula:
Figure BDA0002954736680000023
and
Figure BDA0002954736680000024
s5, substituting data, wherein the method comprises the steps of determining the number N of the winding wires according to the number N of the movable pulleys, determining the mass M of the weight according to the mass M of the carrier rocket and a certain multiplication ratio, and substituting the number N of the winding wires, the mass M of the carrier rocket and the mass M of the weight into the acceleration formula in the step S4 and assigning values to determine the acceleration of the carrier rocket and the acceleration of the weight respectively;
and again based on velocity displacement formula v2Respectively setting the movement distances of the carrier rocket and the weights as 2as and assigning values to respectively determine the initial speeds of the carrier rocket and the weights;
and S6, accelerating the carrier rocket by the self weight of the heavy object according to the determined values of the acceleration and the initial speed in the step S5, releasing the rope on the carrier rocket after the carrier rocket reaches the initial speed value, and igniting and launching the rope.
Further, the pulley block type rocket launching method further comprises the following steps: the movable pulley quantity of movable pulley group is the even number, and the movable pulley quantity of upper pulley group is unanimous with the movable pulley quantity of lower pulley group, and in addition with a plurality of movable pulleys in upper pulley group and the lower pulley group respectively through the connecting rod connection, wherein, the top of upper pulley group is fixed on the building through the mode of hanging, and the top of lower pulley group is through the end-to-end connection of the mode of hanging and rope.
Further, the pulley block type rocket launching method further comprises the following steps: the rope firstly bypasses the movable pulley on the outer side of the lower pulley block, then bypasses the movable pulley on the outer side of the upper pulley block and sequentially winds the rope, so that the tail end of the rope downwards extends and is connected to the top of the lower pulley block after bypassing the movable pulley on the inner side of the upper pulley block.
Further, the pulley block type rocket launching method further comprises the following steps: and a guide static pulley is additionally arranged between the carrier rocket and the movable pulley block, the guide static pulley is arranged above the lower pulley block and is rotationally connected to the building, and the end part of the rope firstly bypasses the guide static pulley and then bypasses the movable pulley of the lower pulley block.
Further, the pulley block type rocket launching method further comprises the following steps: and (4) substituting multiple groups of data in the step S4, selecting a determined value of an effective range according to the initial speeds of the carrier rocket and the heavy object determined by the multiple groups of data, reversely determining the number n of movable pulleys and the heavy material amount m, and then performing power-assisted assembly on the carrier rocket.
Further, the pulley block type rocket launching method further comprises the following steps: the heavy object is selected as an electromagnetically propelled locomotive, an electromagnetic track is built in the vertical direction, the locomotive is driven to run downwards on the electromagnetic track, and the carrier rocket is pulled to move in an accelerated mode by the dead weight of the locomotive and the electromagnetic propulsion force.
Further, the pulley block type rocket launching method further comprises the following steps: and arranging a brake module between the carrier rocket and the heavy object, connecting part of rope bodies of the ropes into the brake module, and after the ropes on the carrier rocket are released, drawing the heavy object by the brake module through the ropes so that the heavy object is decelerated to stop under the drawing action of the brake module.
According to a second aspect of the embodiment of the invention, the pulley block type rocket launching device comprises a launching frame, a rope, a movable pulley block and a weight, wherein a channel for launching the carrier rocket is arranged on one side of the launching frame, the movable pulley block is installed at the top of the other side of the launching frame in a hanging mode, one end of the rope is connected to the carrier rocket, the other end of the rope is connected to the movable pulley block, the weight is connected to the bottom of the movable pulley block, and the weight pulls the carrier rocket to accelerate through the rope under the action of self weight.
Furthermore, a guide static pulley is installed at the top of the launcher, and the end part of the rope far away from the carrier rocket sequentially bypasses the guide static pulley and the movable pulley block.
The embodiment of the invention has the following advantages: the method adopts a pulley block ejection launching mode, utilizes the dead weight of a heavy object to pre-accelerate a carrier rocket to a certain initial speed in a traction mode before the rocket is ignited so as to save rocket fuel and further promote the effective load of the rocket.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
The structures, ratios, sizes, and the like shown in the present specification are only used for matching with the contents disclosed in the specification, so that those skilled in the art can understand and read the present invention, and do not limit the conditions for implementing the present invention, so that the present invention has no technical significance, and any structural modifications, changes in the ratio relationship, or adjustments of the sizes, without affecting the functions and purposes of the present invention, should still fall within the scope of the present invention.
Fig. 1 is a schematic structural diagram of a first scheme of a pulley block type rocket launching method according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a second scheme of a pulley block type rocket launching method according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a third scheme of a pulley block type rocket launching method according to an embodiment of the present invention.
In the figure: 1. a rope; 2. a movable pulley block; 21. an upper pulley set; 22. a lower pulley block; 3. a weight; 4. a guide static pulley; 5. a launch vehicle.
Detailed Description
The present invention is described in terms of particular embodiments, other advantages and features of the invention will become apparent to those skilled in the art from the following disclosure, and it is to be understood that the described embodiments are merely exemplary of the invention and that it is not intended to limit the invention to the particular embodiments disclosed. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides a pulley block type rocket launching method, which comprises the following steps:
s1, adopting a rope 1 for traction, arranging a movable pulley block 2 on one side of a launcher of a carrier rocket 5, fixing one end of the rope 1 on the carrier rocket 5 through a connecting device capable of controlling separation, and connecting the other end of the rope 1 with a heavy object 3 through the movable pulley block 2;
s2, distributing a plurality of movable pulleys included in the movable pulley block 2, dividing the movable pulley block 2 into an upper pulley block 21 and a lower pulley block 22 which are arranged oppositely in the vertical direction, sequentially winding one end of the rope 1 far away from the carrier rocket 5 on the movable pulleys of the movable pulley block 2 in an outward-inward winding manner, and setting the number of the movable pulleys of the movable pulley block 2 to be N and the number of the windings to be N, and taking N to be N + 1;
wherein, the movable pulley quantity of movable pulley group 2 is the even number, and the movable pulley quantity of upper pulley group 21 is unanimous with the movable pulley quantity of lower pulley group 22, passes through the connecting rod respectively with a plurality of movable pulleys in upper pulley group 21 and the lower pulley group 22 in addition and connects to fix the top of upper pulley group 21 on the building through the mode of hanging, and pass through the mode of hanging and the end connection of rope 1 with the top of lower pulley group 22. Based on the arrangement mode, the rope 1 firstly passes through the movable pulleys on the outer side of the lower pulley 22 group and then passes through the movable pulleys on the outer side of the upper pulley group 21 along the direction from bottom to top, and is sequentially wound, so that the tail end of the rope 1 passes through the movable pulleys on the inner side of the upper pulley group 21 and then extends downwards and is connected to the top of the lower pulley group 22;
preferably, a static guide pulley 4 is additionally arranged between the carrier rocket 5 and the movable pulley block 2, the static guide pulley 4 is arranged above one side of the lower pulley block 22 and is rotatably connected to the building, and the end part of the rope 1 firstly passes by the static guide pulley 4 and then passes by the movable pulley of the lower pulley block 22.
S3, providing a power assisting source, wherein the power assisting source comprises the steps that a weight 3 is arranged below a movable pulley block 2, the weight 3 is connected to the bottom end of a lower pulley block 22, the weight 3 is driven to drive a rope 1 to pull a carrier rocket 5 to pre-accelerate in the vertical upward direction under the action of self weight, the mass of the weight 3 is set to be M, and the mass of the carrier rocket 5 is set to be M;
s4, simulating data, including setting the moving distance of the carrier rocket 5 as S1Time of exercise t1At a speed v of movement1Acceleration of motion of a1；
And the movement distance of the weight 3 is S2Time of exercise t2At a speed v of movement2Acceleration of motion of a2；
Based on the condition of neglecting the gravity and the friction force of the rope 1 and the pulley, the stress analysis is carried out to obtain: t is t1＝t2，S1＝NS2，v1＝Nv2，a1＝Na2；
Figure BDA0002954736680000061
Based additionally on the velocity-displacement formula v2Available as 2 as:
thus, it follows:
Figure BDA0002954736680000062
further derive the acceleration formula:
Figure BDA0002954736680000063
and
Figure BDA0002954736680000064
s5, substituting data, wherein the method comprises the steps of determining the number N of windings according to the number N of movable pulleys, determining the mass M of the weight 3 according to a certain multiplication ratio according to the mass M of the carrier rocket 5, and substituting the number N of windings, the mass M of the carrier rocket 5 and the mass M of the weight 3 into the acceleration formula in the step S4 and assigning values to determine the acceleration of the carrier rocket 5 and the acceleration of the weight 3 respectively;
and again based on velocity displacement formula v2Setting the moving distances of the carrier rocket 5 and the weights 3 as 2as respectively, and assigning values to determine the initial speeds of the carrier rocket 5 and the weights 3 respectively;
s6, according to the determined values of the acceleration and the initial velocity in the step S5, the carrier rocket 5 is accelerated by the self weight of the heavy object 3, and after the carrier rocket 5 reaches the initial velocity value, the rope 1 on the carrier rocket 5 is released and ignited for launching;
preferably, in step S4, multiple sets of data may be substituted, and after the initial velocities of the launch vehicle 5 and the weight 3 are determined according to the multiple sets of data, the determination value of the effective range is selected, the number n of the movable pulleys and the mass m of the weight 3 are determined in the reverse direction, and then the power-assisted assembly of the launch vehicle 5 is performed.
Wherein, the weight 3 can be a weight or an electromagnetically propelled locomotive, and when the weight 3 is selected to be the electromagnetically or electrically propelled locomotive, an electromagnetic track is built, so that the locomotive runs on the electromagnetic track, and the carrier rocket 5 is pulled to accelerate by the dead weight of the locomotive and the propelling force of the electromagnetism or the electricity. The scheme has no power limitation on the electrical equipment of the electromagnetic ejection device, can directly utilize the existing electromagnetic technology, and can avoid the weight increase of the carrier rocket 5 caused by the installation of the electromagnetic device on the carrier rocket 5.
As described above:
a preferred embodiment one: when n is equal to 0, that is, the number of the movable pulleys is 0, at this time, after one end of the rope 1 far from the launch vehicle 5 rounds the guide stationary pulley 4, the rope is directly connected with the weight 3, the launch vehicle 5 is accelerated upwards by utilizing the downward gravity of the weight 3, as shown in fig. 1, and the force is analyzed to obtain:
Figure BDA0002954736680000071
substituting n-0 into the formula yields:
Figure BDA0002954736680000072
when M is 2M, the compound is,
Figure BDA0002954736680000073
when M is 10M, the compound is,
Figure BDA0002954736680000074
and (4) conclusion: as the mass of the weight 3 increases gradually, the acceleration a1 of the launch vehicle 5 can only approach g indefinitely.
If the weight 3 is selected as the electromagnetic locomotive, and the traction force of the locomotive is F, then:
F+mg-Mg＝(m+M)a1；
namely a1＝(F+mg-Mg)/(m+M)；
In the case where the mass of the locomotive is not considered,
i.e. m is 0, then
Figure BDA0002954736680000075
At this time, if F>Mg is then a1＞0；
If F>10Mg then a1＞9g；
When M is assumed to be M;
a1＝F/2M；
at this time, if F>Mg, then a1＞g；
If F>10Mg then a1＞5g；
That is, in this embodiment, the smaller the mass m of the weight, the better.
A preferred embodiment two: when n is 1, i.e. the number of movable pulleys is 1, the rope 1 is moved awayOne end of the carrier rocket 5 rounds the guide static pulley 4 and then is connected with the weight 3 through a movable pulley, and the carrier rocket 5 is accelerated upwards by utilizing the downward gravity of the weight 3, as shown in figure 2. Let the moving distance of the carrier rocket 5 be S1Time of exercise t1At a speed v of movement1Acceleration of motion of a1；
And the movement distance of the weight 3 is S2Time of exercise t2At a speed v of movement2Acceleration of motion of a2；
With reference to fig. 2, N + 1-2 is substituted to obtain: t is t1＝t2，S1＝2S2，v1＝2v2，a1＝2a2；
According to the law of conservation of energy, the following can be obtained:
Figure BDA0002954736680000081
wherein:
MgS1representing the gravitational potential energy change of the launch vehicle 5;
mgS2represents the change of the gravitational potential energy of the weight 3, which is given a negative sign since its gravitational potential energy is reduced;
Figure BDA0002954736680000082
representing the kinetic energy variation of the launch vehicle 5;
Figure BDA0002954736680000083
representing the change in kinetic energy of the weight 3;
substitution into S1＝2S2，v1＝2v2In the above formula, the method is simplified and obtained
Figure BDA0002954736680000084
From the formula v2Available aS 2 aS:
Figure BDA0002954736680000085
Figure BDA0002954736680000086
and is
Figure BDA0002954736680000087
When M is 2M, a1＝0；
When M is 10M, the compound is,
Figure BDA0002954736680000088
when M is 20M, the compound is,
Figure BDA0002954736680000091
when M is 100M, the number of the metal ions is 100M,
Figure BDA0002954736680000092
compared with the first scheme, the second scheme can realize that the acceleration breaks through 1g by increasing the weight of the weight 3, but cannot break through 2 g.
Assuming that S is 1000 m, when a1When 1.5g, represented by formula v2Available aS 2 aS:
Figure BDA0002954736680000093
if the heavy object 3 is changed into an electromagnetic locomotive, and the locomotive traction force is F, then:
F+mg-2(Mg+Ma1)＝ma2；
substitution into a1＝2a2The following can be obtained: f + Mg-2(Mg +2 Ma)2)＝ma2；
The method is simplified to obtain: f + (M-2M) g ═ M +4M) a2；
Figure BDA0002954736680000094
When M is 2M，
Figure BDA0002954736680000095
Compared with the first scheme, the second scheme has slightly poor electromagnetic acceleration effect.
A preferred embodiment is three: the weight 3 is suspended by a set of movable pulleys, and for example, as shown in fig. 3, when the number of the movable pulleys is set to four, that is, N +1 is 5, the end of the rope 1 remote from the launch vehicle 5 is passed around the stationary guide pulley 4 and then connected to the weight 3 by a set of movable pulleys, and the launch vehicle 5 is accelerated upward by the downward gravity of the weight 3.
Let the moving distance of the carrier rocket 5 be S1Time of exercise t1At a speed v of movement1Acceleration of motion of a1；
And the movement distance of the weight 3 is S2Time of exercise t2At a speed v of movement2Acceleration of motion of a2；
With reference to fig. 3, N +1 +5 is substituted to obtain: t is t1＝t2，S1＝5S2，v1＝5v2，a1＝5a2；
Then
Figure BDA0002954736680000101
And is
Figure BDA0002954736680000102
When m is2＝5m1When a1＝0。
When m is2＝10m1Time of flight
Figure BDA0002954736680000103
When m is2＝20m1Time of flight
Figure BDA0002954736680000104
When m is2＝100m1Time of flight
Figure BDA0002954736680000105
Compared with the second scheme, the third scheme can realize that the acceleration breaks through 2g by increasing the weight of the weight 3, but cannot break through 5 g. From this we can conclude that the greater the moment magnification of the pulley block, the greater the acceleration that can be obtained, but the heavier the weight 3 required.
If the weight 3 is selected as an electromagnetic locomotive, and the locomotive traction force is F, then:
F+mg-5(Mg+Ma1)＝ma2；
substitution into a1＝5a2The following can be obtained: f + Mg-5(Mg +5 Ma)2)＝ma2；
The method is simplified to obtain: f + (M-5M) g ═ M +25M) a2；
Figure BDA0002954736680000106
When M is 5M, the compound is,
Figure BDA0002954736680000107
the electromagnetic acceleration effect of the third scheme is very poor compared to the first scheme, from which it can be concluded that the first scheme is more suitable for electromagnetic acceleration and the third scheme is more suitable for gravitational acceleration.
In addition, in case three, S is assumed11000 m when a11.67g, expressed by the formula v2Available aS 2 aS:
Figure BDA0002954736680000108
suppose S14000 m when a1When 3.8g, is represented by formula v2Available aS 2 aS:
Figure BDA0002954736680000109
taking "long mark five" as an example, the takeoff weight of "long mark five" is about 643 tons, and the carrying capacity of the near-ground track is about 25 tons. The time of flight for the rocket to launch into the near-earth orbit is approximately 600 seconds. The weight of the fuel of the rocket can be roughly calculated to be about 600 tons according to the parameters, the weight is calculated according to the flight time of the near-earth orbit launching for 600 seconds, and the average fuel consumption is about 1 ton per second after takeoff. The average acceleration of the rocket was found to be about 13.17m/s2 from a first cosmic velocity of 7.9 km/s. If the launch vehicle 5 can be pre-accelerated to 183m/s before ignition, corresponding to approximately 13.89 tons of fuel burned to produce a speed, the launch vehicle 5 can be fed 13.89 tons less fuel and the payload increased by 13.89 tons, i.e., the payload can be increased by 56%. If the carrier rocket can be pre-accelerated to 551m/s before ignition, the effective load of the carrier rocket 5 can be increased by about 41.84 tons, namely the effective load can be increased by 167 percent, so the pulley block type rocket launching method has great practical value for launching the carrier rocket 5.
Another preferred embodiment comprises: a brake module is arranged between a carrier rocket 5 and a heavy object 3, part of rope bodies of the ropes 1 are connected into the brake module, after the ropes 1 on the carrier rocket 5 are released, the brake module pulls the heavy object 3 through the ropes 1, and the heavy object 3 is decelerated to stop under the traction action of the brake module.
Another preferred embodiment comprises: the embodiment of the invention also provides a pulley block type rocket launching device, and the pulley block type rocket launching method based on the embodiment with reference to fig. 1 comprises a launching frame, a rope 1, a movable pulley block 2 and a weight 3, wherein a channel for launching the carrier rocket 5 is arranged on one side of the launching frame, the movable pulley block 2 is arranged at the top of the other side of the launching frame in a hanging mode, one end of the rope 1 is connected with the carrier rocket 5, the other end of the rope is connected with the movable pulley block 2, and the weight 3 is connected to the bottom of the movable pulley block 2, so that the weight 3 pulls the carrier rocket 5 through the rope 1 to pre-accelerate under the action of self weight. In addition, in order to ensure the traction stability of the rope 1, a guide static pulley 4 is installed at the top of the launcher, the end part of the rope 1 far away from the carrier rocket 5 sequentially bypasses the guide static pulley 4 and the movable pulley block 2, and a group of pulley block type rocket launching devices can be respectively arranged at two sides of the carrier rocket 5. Wherein, a mountain body with stable geology and relatively high height is selected as a launcher body, or a launcher with the height reaching thousands of meters is constructed (the existing high mountain or canyon can be used).
Preferably, after the installation angle of the device is adjusted, the device is pulled by a spring or a motor and can eject the airplane, and the airplane can shorten the running distance, promote the takeoff load, save the fuel of the airplane and prolong the flight time under the combined action of the thrust and the traction of the engine of the airplane.
The embodiment of the invention adopts a pulley block ejection launching mode, utilizes the self weight of the heavy object 3, pre-accelerates the carrier rocket 5 to a certain initial speed in a traction mode before the rocket is ignited so as to save rocket fuel and further promote the effective load of the rocket, and the scheme of the embodiment can also be used as an airplane ejection technical scheme of an aircraft carrier or a cave hangar.
Although the invention has been described in detail above with reference to a general description and specific examples, it will be apparent to one skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.

Claims (9)

1. A pulley block type rocket launching method is characterized by comprising the following steps:
s1, adopting a rope for traction, arranging a movable pulley block on one side of a launcher of the carrier rocket, fixing one end of the rope on the carrier rocket through a connecting device capable of controlling separation, and connecting the other end of the rope with a heavy object through the movable pulley block;
s2, distributing a plurality of movable pulleys contained in the movable pulley block, dividing the movable pulley block into an upper pulley block and a lower pulley block which are oppositely arranged in the vertical direction, sequentially winding one end, far away from the carrier rocket, of a rope on the movable pulleys of the movable pulley block in an outward-inward winding mode, setting the number of the movable pulleys of the movable pulley block to be N, setting the number of the windings to be N, and taking N to be N + 1;
s3, providing a power assisting source, wherein the power assisting source comprises a weight arranged below a movable pulley block, one end, far away from the carrier rocket, of a rope is connected with the weight through the movable pulley block, the rope is driven to pull the carrier rocket to pre-accelerate in the vertical upward direction based on the self-weight effect of the weight, the mass of the weight is M, and the mass of the carrier rocket is M;
s4, simulating data, including setting the moving distance of the carrier rocket as S1Time of exercise t1At a speed v of movement1Acceleration of motion of a1；
And the movement distance of the weight is S2Time of exercise t2At a speed v of movement2Acceleration of motion of a2；
And (3) analyzing and obtaining the following stress under the condition of neglecting the gravity and the friction force of the rope and the pulley: t is t1＝t2，S1＝NS2，v1＝Nv2，a1＝Na2；
According to the law of conservation of energy, the following can be obtained:
Figure FDA0002954736670000011
and simplified to obtain:
Figure FDA0002954736670000012
based additionally on the velocity-displacement formula v2Available as 2 as:
Figure FDA0002954736670000013
further derive the acceleration formula:
Figure FDA0002954736670000014
and
Figure FDA0002954736670000015
s5, substituting data, wherein the method comprises the steps of determining the number N of the winding wires according to the number N of the movable pulleys, determining the mass M of the weight according to the mass M of the carrier rocket and a certain multiplication ratio, and substituting the number N of the winding wires, the mass M of the carrier rocket and the mass M of the weight into the acceleration formula in the step S4 and assigning values to determine the acceleration of the carrier rocket and the acceleration of the weight respectively;
and again based on velocity displacement formula v2Respectively setting the movement distances of the carrier rocket and the weights as 2as and assigning values to respectively determine the initial speeds of the carrier rocket and the weights;
and S6, accelerating the carrier rocket by the self weight of the heavy object according to the determined values of the acceleration and the initial speed in the step S5, releasing the rope on the carrier rocket after the carrier rocket reaches the initial speed value, and igniting and launching the rope.
2. The method of claim 1, wherein the method further comprises: the movable pulley quantity of movable pulley group is the even number, and the movable pulley quantity of upper pulley group is unanimous with the movable pulley quantity of lower pulley group, and in addition with a plurality of movable pulleys in upper pulley group and the lower pulley group respectively through the connecting rod connection, wherein, the top of upper pulley group is fixed on the building through the mode of hanging, and the top of lower pulley group is through the end-to-end connection of the mode of hanging and rope.
3. The method of claim 2, wherein the method further comprises: the rope firstly bypasses the movable pulley on the outer side of the lower pulley block, then bypasses the movable pulley on the outer side of the upper pulley block and sequentially winds the rope, so that the tail end of the rope downwards extends and is connected to the top of the lower pulley block after bypassing the movable pulley on the inner side of the upper pulley block.
4. The method of claim 3, wherein the method further comprises: and a guide static pulley is additionally arranged between the carrier rocket and the movable pulley block, the guide static pulley is arranged above the lower pulley block and is rotationally connected to the building, and the end part of the rope firstly bypasses the guide static pulley and then bypasses the movable pulley of the lower pulley block.
5. The method of claim 1, wherein the method further comprises: and (4) substituting multiple groups of data in the step (S4), acquiring initial speeds of multiple groups of carrier rockets and weights according to the multiple groups of data, selecting a determined value of an effective range, reversely determining the number n of movable pulleys and the weight m of heavy materials, and then performing power-assisted assembly on the carrier rockets.
6. The method of claim 1, wherein the method further comprises: the heavy objects are selected to be an electromagnetic or electric propulsion locomotive, a track is built, the locomotive is driven to run on the track by electromagnetism or electricity, and the carrier rocket is pulled to accelerate by the dead weight of the locomotive and the electromagnetic propulsion force.
7. The method of claim 1, wherein the method further comprises: the method comprises the steps that a brake module is arranged between a carrier rocket and a heavy object, part of rope bodies of ropes are connected into the brake module, after the ropes on the carrier rocket are released, the brake module pulls the heavy object through the ropes, and the heavy object is decelerated to stop under the traction effect of the brake module.
8. A pulley-block-type rocket launching device, which adopts the pulley-block-type rocket launching method of any one of claims 1 to 7, and is characterized in that: the pulley block type rocket launching device comprises a launching frame, a rope, a movable pulley block and a weight, wherein a channel for running of a carrier rocket is formed in one side of the launching frame, the movable pulley block is installed at the top of the other side of the launching frame in a hanging mode, one end of the rope is connected to the carrier rocket, the other end of the rope is connected to the movable pulley block, the weight is connected to the bottom of the movable pulley block, and the weight pulls the carrier rocket to accelerate in advance through the rope under the action of self weight.
9. The pulley-set rocket launching device of claim 8, wherein: the top of the launcher is provided with a guide static pulley, and the end part of the rope far away from the carrier rocket sequentially bypasses the guide static pulley and the movable pulley block.
CN202110222501.4A 2021-02-26 2021-02-26 Pulley block type rocket launching method and device Withdrawn CN112896563A (en)

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1299764A (en) * 1999-12-13 2001-06-20 徐志军 Boosting rocket launching method of launching pad
US6354182B1 (en) * 2000-04-18 2002-03-12 Philip J. Milanovich Launch assist system
US20050082424A1 (en) * 2003-10-20 2005-04-21 Masatada Yamamoto Flying vehicle-launching apparatus and method
JP2014141234A (en) * 2013-01-22 2014-08-07 Yukio Ishiyama Auxiliary apparatus for launching of rocket
CN104386259A (en) * 2014-11-14 2015-03-04 侯小红 Host of pulley block ejector
US20150101479A1 (en) * 2013-07-25 2015-04-16 Alexander Dankwart Essbaum Rocket launch tower
CN107606993A (en) * 2017-10-26 2018-01-19 河南师范大学 A kind of carrier rocket launches device for assisting in lifting
CN211893698U (en) * 2020-03-27 2020-11-10 魏永久 Rocket launching pad

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1299764A (en) * 1999-12-13 2001-06-20 徐志军 Boosting rocket launching method of launching pad
US6354182B1 (en) * 2000-04-18 2002-03-12 Philip J. Milanovich Launch assist system
US20050082424A1 (en) * 2003-10-20 2005-04-21 Masatada Yamamoto Flying vehicle-launching apparatus and method
JP2014141234A (en) * 2013-01-22 2014-08-07 Yukio Ishiyama Auxiliary apparatus for launching of rocket
US20150101479A1 (en) * 2013-07-25 2015-04-16 Alexander Dankwart Essbaum Rocket launch tower
CN104386259A (en) * 2014-11-14 2015-03-04 侯小红 Host of pulley block ejector
CN107606993A (en) * 2017-10-26 2018-01-19 河南师范大学 A kind of carrier rocket launches device for assisting in lifting
CN211893698U (en) * 2020-03-27 2020-11-10 魏永久 Rocket launching pad

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