FORM 2
THE PATENTS ACT, 1970 (39 OF 1970)
AS AMENDED BY PATENTS (AMENDMENT) ACT, 2005
AND THE PATENTS RULES, 2006
COMPLETE SPECIFICATION
(See Section 10 and Rule 13)
Title of the invention:
ANTI HAIL ROCKETS WITH EJECTABLE PYROTECHNIQUE CARTRIDGES
Applicant:
Indian Council Of Agricultural Research
Reg. Off: Krishi Bhavan, New Delhi 110001
Address for service: Central Institute For Research On Cotton Technology
(CIRCOT), Indian Council of Agricultural Research, DARE, Govt. of India, Adenwala
Road, Matunga, Mumbai 400019, Maharashtra, INDIA
The following specification describes the invention and more particularly the manner
in which it is to be performed.
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[000] FIELD OF THE INVENTION
[001] The present invention relates generally to anti hail rockets and specifically
relates to design and development of a hail suppression rocket with ejectable
pyrotechnique cartridges.
[002] REFERENCES TO PRECEDING APPLICATIONS
[003] This application derives benefit of provisional application No.
1323/MUM/2012 filed on 25 October 2012 the contents of which are
incorporated in entirety herein by reference.
[004] BACKGROUND OF THE INVENTION
[005] Hail is a potentially devastating force of nature. It can tear cars apart and rip
through houses. The balls of ice can rain down destruction and fill lives with
woe. The mysterious ice particles seem to randomly pop up throughout the
country, making it difficult to predict when and where it will fall. Though it may
seem enigmatic, hail can only form and fall under certain, very specific
conditions.
[006] In many areas of the world hail does enormous destruction to agriculture,
particularly fruit orchards and grain fields. There have been cloud-seeding
projects aimed at reducing hail damage. Some operations have attempted to
put so many nuclei into the supercooled parts of cumulonimbus that they
would be almost totally converted to ice crystals. Such a procedure, called
overseeding, is not considered practical because of the large quantities of
material needed to seed the clouds over an area great enough to have an
appreciable effect. Therefore, it is a pressing need of art to devise
appropriate methods for tracking of hail-forming cloud for deliberate
intervention to prevent or reduce damage causing hail formation.
[007] Hail prevention as part of Natural Disaster reduction activity is of great public
and economic importance to any country in the world. The latest scientific
and technical achievements of Russian rocket seeding technology are
realized in an Operational Hail Protection and Research Program in the
Province of Mendoza, Argentina. Digitized MRL-5 weather radars (X and S
bands) operate under a Computer software control and allow the recording of
storm data on CDs for further reviewing of the operations. Software
calculates the seeding area, how many rockets should be launched for
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covering the seeding area, which launching sites are going to intervene in the
action, as well as the azimuth angles for firing off the rockets. All these
decisions could be adjusted by the operator, depending on his own
experience and skill. The hail suppression project in Bulgaria starts with
protection of about 250 000 ha and since 1987 the protected area reaches 1
500 000 ha. In the beginning Russian rockets are used like “PGI”, “Oblako”,
“Alazan” , which carry an active reagent based on lead iodide, and a
Georgian methodology for hail clouds identification and their seeding. By
seeding hail bearing cloud with silver iodide crystallisation nuclei, the number
of potential deposition cores is increasing, since silver iodide also crystallises
in a hexagonal grid like ice; thus, its small crystals will serve as additional
deposition cores around which molecules of (supercooled) water vapor will
collect while it is expected that ice crystals grow on additional cores as on
natural cores, so that each hail grain will grow less and melt as it falls down
and smaller sized hail and/or rain will fall instead of larger hail. This
hypothesis and the method based on it are applied in Vojvodina by the use of
meteorological radars and rockets. Radars identify hail clouds and rockets
are used for the injection and seeding of silver iodide from the ground into the
clouds. Rockets reach the height of 6-8 km and each rocket contains 400 g of
silver iodide (Vujović et al., 2007). It is very clear that they are not using any
ejectable flares to seed the clouds, instead they are ejecting fumes just like
rocket exhaust and also they don’t have any control where to eject the fumes,
it means the fumes will comes out automatically after 9th second of flight
duration. Because of these reasons they are not able to control the Hail
damages completely
[008] The Anti Hail Rocket systems are used in Bulgaria, Russia, Yugoslavia,
China, Serbia, etc. They have developed the dual-mode engine rockets and
currently they are using these types of rockets for anti hail operations. In
dual-mode engines rocket the first mode is starting, without ice-nucleation
composition in structure of a fuel and the second mode is mid-flight which will
produce Ice-nucleation composition to enhance precipitation. Actually they
are seeding the clouds by following method (Bulgarian method), after
launching, the rocket engine works for 8 seconds and then it ignites the
reagent or the cloud seeding mass for next 30 seconds. For 65 degrees
launching the actual cloud seeding starts at 2200 m altitude. The process
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takes usually 30 seconds and it finishes by self destruction of the rocket. Self
destruction is done by two separated self destructing devices or so called
"timers" which are holding 4 grams of explosive and are activating
themselves at the 38th second of the launching.
[009] However, the efficiency of rockets used and their payloads is minimal,
leading to need of art for more efficient, precise and accurate rocket systems.
From elaborations above, it may be appreciated that existing solutions have
not been fully effective in addressing the need of the art. The present
inventor, in cognizance of aforesaid needs and technical problems, has
undertaken focused research and come up with novel solution to address the
same. The following brief description presents one way of performing the
present invention.
[010] OBJECTS OF THE PRESENT INVENTION
[011] The principle object of the present invention is to provide a hail suppression
rocket with ejectable pyrotechnique cartridges to launch the vehicle for
transporting cloud seeding chemical reagents to the clouds to enhance cloud
condensing nuclei and/or suppressing Hail growth.
[012] Another object of the present invention is to accurately locate and track the
hail-forming cloud, in that its speed, direction and determine its reaction time
[013] Another object of the present invention is to
[014] These objects, together with other objects and advantages which will become
subsequently apparent, reside in the details of preparation and application as
more fully hereinafter described and claimed, reference being had to the
accompanying drawings and detailed description to follow herein.
[015] BRIEF DESCRIPTION OF THE DRAWINGS
[016] Table 1 conveys Anti hail rockets Technical specifications
[017] Table 2 conveys Estimations for Total Impulse, It = 12,000 NS
[018] Table 3 conveys Estimations for Total Impulse, It = 13,500 NS
[019] Table 4 conveys Estimations for Total Impulse, It = 14,000 NS
[020] Table 5 conveys Estimations for Total Impulse, It = 14,000 NS and
deadweight 8 Kg
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[021] Table 6 conveys Design parameters for anti-hail rockets
[022] Table 7 conveys FLIGHT simulation results for anti-hail rockets
[023] Fig 1 illustrates construction of AgI Rocket
[024] Fig 2 illustrates construction of NaCl Rocket
[025] Fig 3 illustrates construction of AgI Rocket (Fins unfolded State)
[026] Fig 4 illustrates construction of AgI Rocket (Fins folded State)
[027] Fig 5 illustrates construction of AgI Rocket - Payload Ejection (Panel
opening)
[028] Fig 6 illustrates construction of AgI Rocket - Payload Ejection
[029] Fig 7 illustrates construction of NaCl Rocket (Fins folded State)
[030] Fig 8 illustrates construction of NaCl Rocket (Fins unfolded State)
[031] Fig 9 illustrates AgI Rocket Payload ejection mechanism
[032] Fig 10 illustrates NaCl Rocket Payload ejection mechanism
[033] Fig11 illustrates AgI Cartridge ejection system
[034] Fig 12 illustrates NaCl payload ejection system
[035] A better understanding of the objects, advantages, features, properties and
relationships of the present invention will be obtained from the following brief
description and accompanying drawing which set forth an illustrative
preferred embodiment and which is indicative of the various ways in which
the principles of the invention may be employed
[036] DETAILED DESCRIPTION OF THE INVENTION
[037] In view of the foregoing disadvantages inherent in the prior art, the general
purpose of the present invention, which will be described subsequently in
greater detail, is to provide a hail suppression rocket with ejectable
pyrotechnique cartridges which has all the advantages of the prior art and
none of the disadvantages.
[038] In this respect, before explaining at least one embodiment of the invention in
detail, it is to be understood that the invention is not limited in its application
to the details of construction and to the arrangements of the components set
forth in the following description or illustrated in the drawings. The invention is
capable of other embodiments and of being practiced and carried out in
various ways. Also, it is to be understood that the phraseology and
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terminology employed herein are for the purpose of description and should
not be regarded as limiting.
[039] According to principles of the present invention, the cloud seeding Rocket
system proposed herein comprises of solid propellant rocket motor as
propelling device and cloud seeding agents as dart/payload. The main
objective of the system is to launch the vehicle for transporting cloud seeding
chemical reagents to the clouds to enhance cloud condensing nuclei and/or
suppressing Hail growth. Accordingly, two types of rockets are proposed to
deliver the chemical reagents into the clouds at different altitudes for cloud
seeding. Cold cloud seeding by higher altitude (up to 12 Km) rocket namely
AgI rocket and Warm cloud seeding by lower altitude (nearly Km) rocket
namely NaCl rocket. Table 1 conveys Anti hail rockets Technical
specifications. Table 6 conveys Design parameters for anti-hail rockets and
Table 7 conveys FLIGHT simulation results for anti-hail rocket.
[040] To identify the exact target and eject the payload in correct location GNSS
chip (receiver) and Central Control System (control programmer) are used as
the rockets proposed are would otherwise be of non-guided missile type.
Once the rocket is fired the user cannot have the control on the rocket. To
address this shortcoming, the inventor herein has developed a
software/control program called central control system (CCS) to control all
the stages of mission like payload ejection at targeted altitude and self
destruction of rocket after completing the mission.
[041] A] AgI Rocket Design:
[042] Fig 1 illustrates construction of AgI Rocket. According to one aspect of the
present invention, Ammonium perchlorate composite propellant (APCP) is
chosen as it gives higher specific impulse when compared to other solid
propellants. Trimodal fraction mixture of ammonium perchlorate(AP) is used
as oxidizer with the mean particle diameter 0f 200μm,400μm and 80μm. In
one embodiment, propellant composition used was:
a) Ammonium perchlorate (oxidizer) = 69% [mass fraction: 200μm »
15.94%, 400μm » 23.12% and 80μm » 29.95%]
b) HTPB R20LM (binder) = 11.9%
c) Aluminium powder (metallic fuel) = 14%
d) DOA (Plasticizer) = 4.25%
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e) Mondur MR (curing agent) = 1.36%
[043] With CP Technologies CHEM Software for rocket motor performance,
internal ballistic characteristics of propellant were:
a) Propellant density (rho) = 1791 Kg/m3
b) Adiabatic flame temperature (Tf) = 3103 K
c) Characteristic velocity (C*) = 1514 m/s
d) Gamma (γ) = 1.205
e) Specific Impulse (Isp) [frozen] = 254.1 Sec
f) (Isp) [Shifting] = 257 sec
g) Molecular weight (M) = 25.72
h) Gas constant (R) = 323 J/kgK
[044] As known from the art, total impulse can only tell motor's capacity to propel a
rocket skyward. Although thrust is an important for characterizing the lift
capability of a rocket motor, it provides no indication of how high the rocket
will be propelled. For this, one needs a measure of the total output in terms of
propulsion capability. The essential yardstick for this is the Total Impulse of
the rocket motor, which incorporates the essential element of time, or thrust
duration. According to further characterization experiments carried out, total
impulse required for our rocket to reach 12 Km altitude with 3 Kg payload
was determined using CP Technology’s FLIGHT Software (Version 2.4) with
parameters identified as Average Thrust, Motor run time, Diameter of the
rocket, Rocket dead mass, Motor mass ratio, Propellant mass, Total motor
mass, Mass of inert, Total mass of rocket, Drag co-efficient out of which the
parameters available for designing were optimized as under:
a) Diameter of the rocket, D = 10 Cm
b) Rocket dead mass, md = 7 Kg (Payload mass 3 K and Structural
mass 4 Kg)
c) Motor mass ratio, f = 0.7
d) Drag co-efficient, Cd = 0.4
e) Motor run time, tb = 4 Sec
f) Total impulse, It
[045] Tables 2 to 4 convey Estimations for Total Impulse, when It = 12,000 NS,
13500 NS, 14000 NS respectively.
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[046] Burn time calculation: The combustion chamber outer diameter is 90 mm,
after considering wall thickness and linear thickness the space available for
grain outer diameter is 82 mm and ideal density of the propellant is 1791
kg/m3 .To avoid erosive burning perforation diameter was chosen as 20 mm
Web thickness = ����������
�� =����������
�� = 31 ����
Now the burn time
���� = ������ ������������������
�������� �������� = ����
��.����
���� = 3.9 ������
���� = 4 ������
rest of the parameters are calculated by using the following relations:
Average thrust, F = ����
����
Propellant mass, mp = ����
��.������
Total motor mass, mm = ����
��
Motor structural mass, mms = mm - mp
Mass of Inert, mI = md – mm
Total mass of the rocket, mt = md + mp
[047] According to another aspect of the present invention, peak altitude for the
rockets proposed was calculated by CP Technologies FLIGHT (two
dimensional trajectory analysis) Software by estimating the required Total
Impulse for the mission of the rockets by taking different values for Total
Impulse. Since it is very difficult to make rest of rocket structural parts within
2 Kg dead mass was increased from 7 Kg to 8 Kg and estimations performed
accordingly. Table 5 conveys Estimations for Total Impulse, It = 14,000 NS
and deadweight 8 Kg. Through the above process, the present inventor has
arrived at optimization of Total Impulse of 14,000 N.Sec with average thrust
of 3500 N for the duration of 4 seconds to reach the desired altitude of 12 Km
necessary for mission of the rockets proposed herein. The final design
parameters and FLIGHF Simulation results are listed in table
[048] According to yet another aspect of the present invention, the gas dynamic
calculations were undertaken with following constants:
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a) Pressure at combustion chamber, Pc = 70 bar (1015 Psi)
b) Exit Pressure, Pe = 1.01325 bar (14.7 Psi)
c) Pressure ratio, Pe/ Pc = 0.014475
d) Adiabatic flame temperature ,Tc = 31030 c
e) Specific gas constant, R = 323 J/Kg.K
f) Specific heat ratio, k = 1.205
[049] By calculations (not shown), following values were determined:
a) Specific Impulse: Isp = 251 Seconds
b) Characteristic velocity: C* = 1541 m/sec
c) Thrust coefficient: Cf = 1.5958
d) Expansion ratio: ε = 8.884
e) Mass flow rate: ��̇ = 1.375 Kg/sec
f) Throat area: At = 3.1033 x 10-4 cm2
g) Throat diameter: Dt = 1.9878 cm
h) Thrust: F = 3344 Newton = 3194 N (after applying correction
factor)
i) Effective exhaust velocity: Ve = 2459 m/sec
j) Rocket velocity: U = 578 m/sec
k) Mach number: M = 1.75
[050] From above, the motor operating conditions were finalized as:
a) Total impulse, It = 14000 N.Sec
b) Average Thrust, T = 3344 N
c) Propellant specific Impulse, Isp = 257seconds
d) Motor operating time, tb = 4 seconds
e) Specific gas constant, R = 323 J/Kg.K
f) Characteristic velocity, C* =1510 m/sec
g) Thrust co-efficient, Cf = 1.5958
h) Expansion ration, ε = 8.884
i) Mass flow rate, ��̇ =1.388 kg/sec
j) Throat area, At = 2.9941x10-4 m2
k) Throat diameter, Dt = 1.95 cm
[051] According to another aspect of the present invention, for nozzle design,
following constants formed basis:
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a) Pressure ratio, ����
����
�� = ��.����������
���� = 0.014475
b) Nozzle throat Area, At = 2.9941 cm2
c) Nozzle throat Diameter, Dt = 1.95 cm
d) Expansion Ratio, ε = 8.884
[052] From above, the nozzle design was finalized as:
a) Exit cone area: Ae = 26.5996 cm2
b) Exit diameter: De = 5.82 cm
c) Cone angle selection: initial angle of 250 and exist angle of 90-130 is
representative of an efficient exit cone contour
d) Length of nozzle divergent section: Ld 7.5 cm
e) Length of nozzle convergent section: L�� = 7 cm
f) Pressure at throat: Pt = 39.445 bar
g) Temperature at throat: T* = 2814 K
h) Density at throat: ���� = 29.7 ����
������
i) Exit Mach number: Me= 3.209
j) Exit gas temperature: Te = 1509.599 K
k) Density at exit: = 0.4486 ����⁄����
l) Divergent loss co-efficient, λ = 0.983
m) For the nozzle section the AISI 4130 steel has been chosen
n) Throat inserts: polycrystalline graphite
o) AISI 4130 stell is choosen for rocket motor case
[053] According to designing aspects of the present invention, the combustion
chamber outer diameter is 90 mm, after considering wall thickness and liner
thickness the space available for grain outer diameter is 82 mm and ideal
density of the propellant is 1635.88 kg/m3. Fig 3 illustrates construction of AgI
Rocket (Fins unfolded State) while Fig 4 illustrates construction of AgI Rocket
(Fins folded State)
[054] On approximation of the nozzle convergent length to the round of value, the
exit cone angle is changing into the exact value of β = 24.230
[055] B] NaCl Rocket Design:
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[056] Fig 2 illustrates construction of NaCl Rocket. Constants for gas dynamic
calculations:
a) Pressure at combustion chamber, Pc = 68 bar
b) Temperature of combustion chamber,Tc = 2464.40 c
c) Specific gas constant, R = 350.654 J/Kg.K
d) Specific heat ratio, k = 1.2251
[057] From above, following parameters were optimized (calculations not shown):
a) Specific impulse: R = 354 J/Kg.K
b) Characteristic velocity: C* = 1506.8 m/sec
c) Thrust coefficient: Cf = 1.582
d) Expansion ratio: ε = 8.363
e) Mass flow rate: ��̇= 0.378 Kg/sec
f) Throat area: At = 0.838 cm2
g) Throat diameter: Dt =1.033 cm
h) Thrust: F = 900.134 Newton
i) Effective exhaust velocity: Ve = 2383 m/sec
j) Nozzle exit Mach number: Me= 3.22
k) Nozzle exit gas temperature: Te = 1264 K
l) Flight speed: U = 283.236 m/sec
m) Flight Mach number: M = 0.858
[058] Accordingly, motor operating conditions were selected as:
a) Total impulse, It = 4500 N.Sec
b) Average Thrust, T = 900 N
c) Propellant specific Impulse, Isp= 243seconds
d) Motor operating time, tb = 5 seconds
e) Specific gas constant, R = 354 J/Kg.K
f) Characteristic velocity, C* =1506.8m/sec
g) Thrust co-efficient, Cf = 1.582
h) Expansion ration, ε = 8.363
i) Mass flow rate, ��̇ =0.378 kg/sec
j) Throat area, At = 8.376*10-5 m2
k) Throat diameter, Dt = 1.033 cm
[059] Nozzle design parameters (calculations not shown) were:
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a) Exit cone area: De= 2.95 cm
b) length of the nozzle after of the throat: Ld= 6 cm
c) Length of the nozzle convergent section: L�� = 4 cm
d) Pressure at throat: Pt = 38 bar
e) Temperature at throat: T*= 2460 K
[060] Combustion chamber length estimations (calculations not shown) were:
a) Required propellant volume: Vp = 1153.7 cm3
b) Perforation Diameter: Dp =1.46 cm
c) Length of the combustion chamber: L= 59 cm
d) Payload Section Length: L ≅ 54 cm
e) Nose cone length: L = 26 cm
[061] According to another aspect of the present invention, aerodynamic fin design
was integrated for ensuring desired flight characteristics to the rocket
proposed. Fig 7 illustrates construction of NaCl Rocket (Fins folded State)
while Fig 8 illustrates construction of NaCl Rocket (Fins unfolded State).
Parameters (calculations not shown) were:
a) Fin length≅ 12 cm
b) Fin span = 14.7 cm
c) Circumference of the fin adapter = 18.85 cm
d) Space available for each fin span = 6.28 cm
e) considering effective span, the span of each fin = 6 cm
[062] C] Payload Ejection Mechanisms
[063] Different types of payload delivery mechanisms for two kinds of rockets
described hereinabove. AgI Rocket has payload ejection by spring
mechanism whereas NaCl Rocket has payload ejection by complete bursting
of rocket. Fig 5 and Fig 9 illustrates construction of AgI Rocket - Payload
Ejection (Panel opening) while Fig 10 illustrates NaCl Rocket Payload
ejection mechanism.
[064] AgI Rocket Payload Ejection Mechanism comprises of a central control
system (CCS), GNSS chip, linear servos and spring mechanism. The
integrated GNSS control circuit initiates the payload to eject at the targeted
altitude. The GNSS receiver provides continual height information to the
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control circuit. Fig11 illustrates AgI Cartridge ejection system and Fig 12
illustrates NaCl payload ejection system. Based on the altitude information
the CCS will release three triggering currents as follows:
Trigger 1:
a) Function: to initiate ignition of two AgI cartridges
b) Timing: 2500 meters before the targeted altitude (trigger altitude = target
altitude – 2500 meters) OR 5 seconds before the target altitude time (i.e.
5 seonds before second trigger) as the rocket speed is 558 m/sec.
c) Voltage Req: 6 volt per cartridge (total 2 cartridges)
Trigger 2:
a) Function: To simultaneously trigger three servo motors at a time
b) Timing: Immediate after reaching the target altitude
c) Voltage Req: 4 to 8 Volt DC per servo (PWM digitally controlled servo
motor, 3 nos.)
Trigger 3:
a) Function: To ignite the self destruction unit for complete bursting of the
rocket
b) Timing: 5 seconds after second trigger
c) Voltage Req: 5 volt per destruction unit (total 2 units)
[065] Payload ejection of AgI Cartridges is shown in fig.8. This Mechanism consists
the following components:
a) GPS chip & Antenna
b) Central control system
c) Power source
d) Rotary Servo Motors (3 nos.)
e) Locking pin (4 nos.)
f) Compression Springs (2 nos.)
g) Ejection panel (2 nos.)
[066] The NaCl rocket delivers the payload by complete bursting of NaCl container
as well as rocket. To achieve this, the payload section of NaCl rocket is
provides with integrated GNSS control circuit that triggers the payload to
burst at the specified height.
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[067] In the two types of rockets referred hereinabove, the payload ejection done
by GNSS based control circuit. This circuit will start to work after receiving
signals from GNSS Satellite as shown in Fig 10(a) and 10(b)
[068] As will be realized, the present invention is capable of various other
embodiments and that its several components and related details are
capable of various alterations, all without departing from the basic concept of
the present invention. Accordingly, descriptions will be regarded as
illustrative in nature and not as restrictive in any form whatsoever.
[069] Modifications and variations of the system and apparatus described herein
will be obvious to those skilled in the art. Such modifications and
variations are intended to come within the scope of the appended claims.

CLAIMS
We claim,
1] An anti-hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes, said rocket comprising:
a) a hollow nose adapted to receive a navigation system within its interior
space, said navigation system being a GPS chip, antenna and a central
control system capable of receiving navigational instructions from a remote
station;
b) a hollow cylindrical section continuing from base of said nose adapted to
contain a payload of at least one each among a pyrotechnique cartridge,
ejection panel, compression springs and trigger mechanism;
c) a rocket motor in continuing from the hollow cylindrical section, said motor
comprising a reservoir for ammonium perchlorate composite propellant, firing
mechanism and nozzle towards distal end of the rocket for escape of hot
gases; and
d) a hollow cylindrical tail portion adapted to receive at least 1 and up to 6
aerodynamic fins on its outward lateral walls and adapted to receive locking
pins, power source, triggering mechanism, compression springs and servo
motors within its interior space which act upon instructions from the
navigation system in said nose to trigger payload delivery and control
orientation of the fins to result in the rocket being directed in the desired
direction intended for cloud seeding and hail suppression purposes.
2] The anti hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes according to claim 1, wherein payload delivery is in
response to three distinct sequential trigger events typified in that:
a) A first trigger when rocket altitude equals target altitude less 2500 meters or 5
seconds before target altitude time where both Silver iodide cartridges are
ignited electrically at 6 volt per cartridge;
b) A second trigger upon reaching the target altitude where three servo motors
are simultaneously triggered electrically at 4 to 8 Volt DC per servo motor
c) A third trigger 5 seconds after the second trigger to ignite the self destruction
unit for complete bursting of the rocket
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3] The anti hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes according to claim 1, wherein the remote station is
selected among satellites and terrestrial weather monitoring bases.
4] The anti hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes according to claim 1, wherein the rocket is
characterized in being dimensioned to a diameter of 100mm, length of 1850mm,
overall weight of 12Kg, length of rocket motor of 835mm, payload section length
of 710mm and nosecone length of 305mm when the seeding material contained
in the rocket is Silver iodide.
5] The anti hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes according to claim 3, wherein payload ejection is by
spring mechanism activated in response to activation signals received from the
remote station.
6] The anti hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes according to claim 3, wherein payload ejection is by
spring mechanism activated in response to predefined parameters of altitude and
time of flight.
7] The anti hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes according to claim 1, wherein the rocket is
characterized in being dimensioned to a diameter of 70mm, length of 1600mm,
overall weight of 7.888Kg, length of rocket motor of 760mm, payload section
length of 580mm and nosecone length of 260mm when the seeding material
contained in the rocket is Silver iodide.
8] The anti hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes according to claim 5, wherein payload ejection is by
complete bursting of the rocket upon attaining a predefined altitude.
9] The anti hail rocket with ejectable pyrotechnique cartridges according to claim 1,
which when deployed, delivers metered quantity of cloud seeding materials at site
intended to cause precipitation and suppression of hail formation.
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10] An anti hail rocket with ejectable pyrotechnique cartridges for cloud seeding and
hail suppression purposes as substantially described herein with reference to the
accompanying description and drawings.
agent for and on behalf of applicant