Abstract:
A method of disposing of a rocket motor  12  comprises burning propellant contained within the motor and generating an enclosure  13  of liquid within which the burning occurs. Apparatus for carrying out the method comprises a nozzle/clamping unit  1  for securing the rocket motor  12  in place and generating the liquid enclosure  13 . The liquid, which may be water and may include neutralising chemicals, is filtered and recycled.

Description:
FIELD OF THE INVENTION 
     The present invention relates to a method and apparatus for rocket motor disposal. 
     BACKGROUND OF THE INVENTION 
     Large numbers of redundant munitions comprising rocket motors exist and environmentally friendly methods for their disposal are sought. 
     British Patent Application No. 2306884 describes a method of limiting the environmental disturbance of an exploding munition, such as a bomb, by spraying a liquid towards the munition to create a liquid dispersion which at least partly surrounds the munition and detonating the munition into the dispersion. That method is suitable for disposing of bombs, but may be unsuitable for disposing of certain rocket motors, despite the fact that these can be detonated or deflagrated without becoming propulsive. 
     SUMMARY OF THE INVENTION 
     It is an aim of the present invention to provide a safe, environmentally friendly and adaptable open burning method and apparatus for disposing of rocket motors. 
     According to one aspect of the invention, there is provided a method for disposing of a rocket motor comprising burning propellant contained within the motor, and generating an enclosure of liquid within which the burning occurs. The enclosure or shroud of liquid captures particulate matter from the rocket motor&#39;s emissions. 
     In an embodiment of the invention, the liquid, which may comprise water, includes at least one neutralising chemical for neutralising noxious substances resulting from the burning and/or for capturing hazardous materials, such as asbestos. 
     Preferably, prior to the burning step, demilitarization or reverse engineering operations are carried out on a rocket-propelled munition of which the rocket motor forms a part. Such operations may comprise removal of a warhead, removal of an ancillary propulsion system and removal of a venturi mechanism. The best results are achieved when the motor is secured in a substantially vertical position, with its rear or exhaust end facing upwards, during the burning step. The method may comprise further steps of filtering liquid from said enclosure and recycling the filtered liquid to the enclosure. 
     According to another aspect of the invention, there is provided apparatus for disposing of a rocket motor, comprising means for generating an enclosure of liquid within which propellant contained within the motor can be burnt. Preferably, the liquid enclosure generating means comprises a nozzle having an outlet in the form of a closed figure, such as a circle. The apparatus preferably comprises means for securing the rocket motor in place. In a particular embodiment, the securing means and the liquid enclosure generating means are integral parts of the same unit. The apparatus preferably includes a pump for conveying liquid to the enclosure generating means. Filtering means for filtering liquid from the enclosure may also be included, as may a submersible pump for returning the liquid to a reservoir from which it may once again be conveyed to the enclosure generating means. Deflecting means, such as a hood and a conduit of large diameter, may optionally be provided for directing the exhaust plume and aerosoled liquid to a non-damaging location. 
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS 
     The present invention will now be described in more detail, by way of example only, with reference to the accompanying drawings, in which: 
     FIG. 1 is an elevation of a nozzle/securing unit according to an embodiment of the invention; 
     FIG. 2 is a plan of the unit shown in FIG. 1; 
     FIG. 3 is a vertical section of the unit shown in FIGS. 1 and 2, taken along the line III—III in FIG. 2; 
     FIG. 4 shows a detail of the second shown in FIG. 3; 
     FIG. 5 schematically shows the unit of FIGS. 1 to  4  in use; and 
     FIG. 6 is a schematic plan of apparatus according jot an embodiment of the invention including the unit of FIGS. 1 to  5 . 
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     FIGS. 1 to  4  show a unit  1  for securing a rocket motor and generating a liquid enclosure around burning propellant from the motor. The unit  1  comprises a frame  2  mounted on an open rectangular base  3 . Adjustable clamps  4  provided on the frame  2  can be tightened to secure a rocket motor in place in the unit  1  with the rear or exhaust end of the motor facing upwards. 
     A pipe  5  mounted in a square around the bottom of the frame  2  has an inlet  6  to which a high-pressure pipeline can be fitted in a liquid-tight manner. A number (eight in this example) of vertical pipes  7  lead from the annular pipe  5  to an annular nozzle  8  mounted around the top of the frame  2 . A detailed cross-section of the nozzle  8  is shown in FIG.  4 . The nozzle has a continuous annular outlet  9  having a radial width of typically 1.5 mm. Larger radial widths can be engineered if greater water flows are required. 
     Prior to the burning of its propellant, demilitarization or reverse engineering operations are carried out on a rocket-propelled munition to be disposed of. Firstly, the warhead (which may or may not be explosive) and any ancillary means of propulsion are removed. Having thusly separated the rocket motor from the missile, it is advisable, but not necessary, to remove the rocket motor&#39;s venturi mechanism. Such removal creates a less energetic exhaust flow and allows the formation of a denser and more easily contained exhaust cloud. If removal of the venturi mechanism is difficult or dangerous, then the apparatus of the invention can be designed to deal with rocket motors still having a venturi mechanism. 
     As shown in FIG. 5, in use, the unit  1  is weighted down by placing heavy weights  10  on the base  3  of the unit. A high-pressure pipeline  11  is connected to the inlet  6 . A rocket motor  12  is then placed in the frame  2  and the clamps  4  are tightened around the rocket motor. Water, optionally containing one or more neutralising chemical or mineral, is then forced through the pipeline  11 , into the annular pipe  5 , up the vertical pipes  7  and out of the outlet  9  of the annular nozzle  8 . In this manner, a cylindrical enclosure  13  of water is formed, completely surrounding the exhaust plume  14  of the rocket motor  12 . The water enclosure  13  captures noxious particulate matter exhausted from the burning propellant and thus keeps such matter on the already contaminated land of a purposely built munitions disposal facility and prevents exhaust emissions from entering the atmosphere. 
     FIG. 6 is a schematic plan of such a facility. Water is supplied from a supply tank  15 , in which pre-mixing of neutralising or decontaminating agents can take place if required, to a high pressure, high volume pump  16 . The pump  16  can be driven by a fuel burning engine or by an electric motor, at least one large diesel engine being preferred for field operations. 
     The pump  16  forces water through the high pressure pipeline  11  to the unit  1 . The area of ground on which the unit  1  is situated is provided with either a suitable pavement or a heavy duty membrane and has a slight gradient running downwards in the direction of the arrows. This means that contaminated water from the enclosure flows into a catchment tank  17  where particles suspended in the water are allowed to settle. The catchment apron optionally includes a chalk or lime bed for neutralising acids from the rocket motor exhaust. 
     A submersible pump  18  is located in the catchment tank  17 , spaced from the bottom of the tank so as to prevent sediment in the tank being drawn into the pump  18 . The submersible pump is preferably hydraulically driven but may alternatively be electric. The pump  18  transfers the water to a filtration plant  19  and thence back to the supply tank  15  via a low pressure pipeline  20 . Filtration beds could alternatively or additionally be included in the catchment tank  17 . Preferably, there are two catchment tanks  17  which are used alternately so that the sediment layer can be periodically recovered, treated and disposed of. 
     While most of the water is recycled as described above, some topping-up of the supply tank  15  will be necessary as a result of evaporation. 
     The apparatus is portable and can be mounted on a trailer assembly for transportation and field use if the movement of rocket motors would present problems of logistics or safety. 
     Preliminary calculations which were used to design a nozzle and clamping unit according to the invention are given below:          Burn                 rate                 m     =         MF   T                   m     =     1.16                   kg/        sec                              
     Assume that the density of the cold exhaust gases would be ρC=1 kg/m3 
     Assume that the exhaust temperature is 3500 K. The volume of gas per second is        vol   =         m   ·     3500   300     ·   ρ                   C                 vol     =     13.55                 m3        /        sec                              
     Guess rocket body diameter DR=0.3 metres                      The                 velocity                 of                 the                 gas                 is                 velG     =         vol     0.25   ·   π   ·     DR   2                       velG     =     191.64                 m        /        sec                                 Rocket                 thrust                                FT     =         m   ·   velG                   FT     =     222.52                 Newtons                                          
     Note that this would be much higher if the gases vent through a Venturi.          The                 working                 pressure                 of                 the                 water                 pump                 is                 P     =       8.5   ·     10   5                     Pascal                         With                 efficient                 nozzles               the                 water                 velocity                         velW     =             2   ·   P     998                     velW     =     41.27                 m        /        sec                                           
     Note that is this fast enough to induce cavitation round any sharp bend so we want a gentlle convergence to the nozzle exit. 
     
       
         
               
               
               
             
               
               
             
               
               
               
               
             
               
               
             
               
               
               
               
             
           
               
                   
               
             
             
               
                 
                   
                     
                       
                         
                           The 
                            
                           
                               
                           
                            
                           area 
                            
                           
                               
                           
                            
                           of 
                            
                           
                               
                           
                            
                           the 
                            
                           
                               
                           
                            
                           water 
                            
                           
                               
                           
                            
                           jet 
                            
                           
                               
                           
                            
                           nozzle 
                            
                           
                               
                           
                            
                           will 
                            
                           
                               
                           
                            
                           be 
                            
                           
                               
                           
                            
                           Anozz 
                         
                         = 
                         
                           Q 
                           velW 
                         
                       
                     
                             
                     
                         
                     
                   
                 
                 Anozz = 1.53 · 10 −3   
                 m2 
               
               
                   
               
               
                 
                   
                     
                       
                         
                           Nozzle 
                            
                           
                               
                           
                            
                           gap 
                            
                           
                               
                           
                            
                           is 
                            
                           
                               
                           
                            
                           t 
                         
                         = 
                         
                           Anozz 
                           
                             π 
                             · 
                             kN 
                             · 
                             DR 
                           
                         
                       
                     
                             
                     
                         
                     
                   
                 
                 t = 1.47 · 10 −3   
                 meters 
               
               
                   
               
             
          
           
               
                   
                 A sensible value would be t = 1.5 mm 
               
             
          
           
               
                 Guess heat of combustion 
                 H = m · 25 · 10 6   
                 H = 2.9 · 10 7   
                 Joules/sec 
               
               
                 Latent heat of water 
                 LH = Q · 1000 · 2.25 · 10 6   
                 LH = 1.42 · 10 8   
                 Joules/sec 
               
               
                   
               
             
          
           
               
                 The ratio of latent heat of boiling to heat in rocket exhaust is 
                 
                   
                     
                       
                         
                           LH 
                           H 
                         
                         = 
                         4.88 
                       
                     
                             
                     
                         
                     
                   
                 
               
               
                   
               
             
          
           
               
                 CONTROL PANEL 
                   
                   
                   
               
               
                 Rocket diameter 
                 DR ≡ 0.3 
                 Burn time 
                 T ≡ 180 
               
               
                 Nozzle to rocket diam. 
                 kN ≡ 1.1 
                 Pump pressure 
                 P ≡ 8.5 · 10 5   
               
               
                 Fuel weight 
                 MF ≡ 209 
                 Pump flow 
                 Q ≡ 0.063 
               
               
                   
               
             
          
         
       
     
     Apparatus including a nozzle/clamping unit was constructed according to these criteria and tested against the live open burning of two rocket motors as a control. About 5 tons of water were pumped through the nozzle per minute. The apparatus achieved a dramatic reduction in exhaust emission. Noise was also greatly reduced and this is a further advantage of the invention. After the test, many tons of contaminated water were found to have been deposited downwind of the burning site. 
     In order to avoid the contaminated water from being carried downwind, a deflecting device in the form of a shroud or hood  21  is provided. (The support for the shroud or hood  21  is omitted). This will catch the contaminated water and direct it to a safe location.