Abstract:
A tubular distributor in a missile having a right-angled hollow tubular first section, the right-angled hollow tubular first section having a first leg and a second leg, a straight hollow tubular second section, an end of the first leg of the right-angled hollow tubular first section perpendicularly connected to a first end of the hollow tubular second section, a straight hollow tubular third section, a first end of the hollow tubular third section perpendicularly connected to the first end of the straight hollow tubular second section, and a close/open valve positioned within the straight hollow tubular third section, the close/open valve positioned between a gas generator and the straight hollow tubular second section.

Description:
BACKGROUND OF THE INVENTION 
     In the past, a post boost control power assembly had a manifold that distributed gas to several integrated thruster valve assemblies. Such a manifold is shown in U.S. Pat. No. 4,550,888. In the &#39;888 patent, the gas was enclosed in the manifold, before the gas was sent from the manifold into the integrated valve assemblies. The gas was used to produce forces on the integrated thruster valve assemblies, as the gas passed out of the integrated thruster valve assemblies. The forces were uses to control position, attitude and velocity of a final stage of a multi-stage rocket. 
     The manifold of the &#39;888 patent obtained gas from a gas generator. Heat was lost from the gas, since the gas was sent through the manifold. The loss of heat from the gas, causing the gas to produce less powerful forces than might be needed for proper propulsion for position, attitude and velocity control. The cooled gases were sent to integrated thruster valve assemblies from the manifold. 
     SUMMARY OF THE INVENTION 
     The disclosed post boost control power assembly has tubular gas distributors. Each tubular gas distributor is connected to two gas generators. Each tubular gas distributor is also connected to an integrated thruster valve assembly. Each tubular gas distributor sends gas directly from a connected gas generator into a single integrated thruster valve assembly. Since gas passes directly through the tubular gas distributor, the gas remains at a high temperature. There is minimal heat loss from the gas that passes through the tubular gas distributor. 
     The gas that passed through a tubular gas distributor produces a more powerful force than is the force that is produced by gas that comes from a manifold, since there is less heat loss from the disclosed post boost control power assembly than from a past post boost control power assembly. 
     The disclosed tubular gas distributor has three ports. A gas generator is connected to a first port of the tubular gas distributor. An integrated thruster valve assembly is connected to a second port of the tubular gas distributor. Another gas generator is connected to a third port of the tubular gas distributor. 
     The disclosed post boost control power assemble has tubular gas distributors, dual gas generators, integrated thruster valve assembles, igniters for igniting each of the dual gas generators and close/open valves. The disclosed post boost power control system forms a loop of tubular gas distributors within an aft section of a body of a missile. 
     Each dual gas generator has two single gas generators. The two single gas generators are joined to form the dual gas generator. Each single gas generator has gas generating material. The two single gas generators are joined together, with the gas generating material separated by a bulkhead wall, to form a dual gas generator. The gas generating material within a single gas generator only burns up to the bulkhead wall. The dual gas generator has two ports, one port for each of the two single gas generators. 
     Gas from four single gas generators, the four gas generators being within two dual gas generators, is sent through four triple port tubular gas distributors during a first phase. Other gas from four other single gas generators, the latter four gas generators being within two other dual gas generators, is sent through the same four triple port tubular gas distributors during a second phase. 
     Four close/open valves are closed so that gas from a first four generators, within two dual gas generators, is sent into the four triple port tubular gas distributors during the first phase. The four close/open valves are opened, so that other gas from a second four gas generators, within two other dual gas generators, is sent into the four triple port tubular gas distributors during the second phase. 
     The use of four tubular gas distributors in a post boost control power assembly provides for less heat loss from gas coming from four single gas generators, than does a post boost control power assembly that uses a manifold connected to the four single gas generators. Therefore greater efficiency in position, attitude and velocity control is produced by the disclosed post boost control power assembly than was available in the past, since the force produced by gas from the tubular gas distributors is greater, and of longer duration, than is a force produced by gas that passes through a manifold. 
     A benefit of the tubular gas distributors, as compared to the prior art manifold, is enhanced by a bulkhead inserted in the center of each dual gas generator. The bulkhead within each dual gas generator allows for eight gas generators being within the disclosed post boost control power assembly. 
     Four gas generators, within two of the four dual gas generators, supplies gas during a first time period. Then another four gas generators, within two other dual gas generators, supplies gas during a second time period. 
     The disclosed post boost control power assembly provides hot gases for use by integrated thruster valve assemblies. The hot gases are used to change the position, attitude and velocity of a final stage of a multi-stage rocket. 
     The combined tubular gas distributor, close/open valve and first and second gas generator provide for a more direct gas flow to an integrated thruster valve assembly, than is provided to an integrated thruster valve assembly by a combined manifold and single gas generator. Further, the gas pressure decrease, due to heat loss, is lessened by use of a gas distributor rather than a manifold. 
    
    
     
       DESCRIPTION OF THE DRAWING 
       FIGURE is a diagrammatic view, looking aft, of a post boost control power assembly, the post boost control assembly being located within a missile. 
     
    
    
     DESCRIPTION OF THE PREFERRED EMBODIMENT 
     FIGURE shows a post boost control power assembly  6 . The assembly  6  is connected to an aft section  8  of a missile body  10  of a missile  11 . The assembly  6  has four tubular gas distributors  12 ,  14 ,  16  and  18 . The assembly  6  has four dual gas generators  20 ,  22 ,  24  and  26 . The assembly  6  has four integrated thruster valve assemblies  28 ,  30 ,  32  and  34 . Four ignition igniters  36 ,  38 ,  40  and  42  are connected to the four dual gas generators  20 ,  22 ,  24  and  26 . 
     The assembly  6  forms a loop  19  of four tubular gas distributors  12 ,  14 ,  16  and  18  within aft section  8  of missile body  8 . The loop  19  is made possible due to a shape of each of the tubular gas distributor  12 ,  14 ,  16  and  18 . 
     Tubular gas distributor  12  has three hollow tubular sections, namely a right-angled hollow tubular first section  46 , a hollow tubular second section  48  and a hollow tubular third section  44 . The tubular gas distributor  12  has a gas flow close/open valve  49  that is located within hollow tubular third section  44 . Hollow tubular sections  44 ,  46  and  48  are made as short as possible, to reduce heat loss from gases that pass through the hollow tubular sections  44 ,  46  and  48  of gas distributor  12 . The hollow tubular sections  44 ,  46  and  48  of tubular gas distributor  12  are round tubes. The hollow tubular sections  44 ,  46  and  48  of gas distributor  12  could alternately be rectangular tubes or square tubes. 
     The right-angled hollow tubular first section  46  has a first leg  43  and a second leg  45 . First leg  43  and second leg  45  are mutually perpendicular. The right-angled tubular first section  58  has a first leg  55  and a second leg  57 . First leg  55  and second leg  57  are mutually perpendicular. The right-angled tubular first section  76  has a first leg  73  and a second leg  75 . First leg  73  and second leg  75  are mutually perpendicular. The right-angled tubular first section  95  has a first leg  91  and a second leg  93 . First leg  91  and second leg  93  are mutually perpendicular. 
     A dual ignition cord igniter  36  is connected to dual port gas generator  20 . A dual ignition cord igniter  38  is connected to dual port gas generator  22 . A dual ignition cord igniter  40  is connected to dual port gas generator  24 . A dual ignition cord igniter  42  is connected to dual port gas generator  26 . 
     Section  46  of tubular gas distributor  12  is connected to a gas generator  50  of dual gas generator  20 . Section  44  of gas distributor  12  is connected to gas generator  52  of dual gas generator  52 . Section  48  of gas distributor  12  is connected to integrated thruster valve assemble  28 . An ignition cord  54  of ignition igniter  36  is connected gas generator  50 . An ignition cord  56  of igniter  40  is connected to a gas generator  52  of dual gas generator  24 . A gas flow close/open valve  49  is located within section  44  of the gas distributor  12 . 
     Section  58  of tubular gas distributor  14  is connected to gas generator  60  of dual port gas generator  22 . Section  62  of gas distributor  14  is connected to gas generator  66  of dual gas generator  24 . Section  68  of gas distributor  14  is connected to integrated thruster valve assembly  30 . A gas flow close/open valve  70  is located within section  62  of gas distributor  14 . An ignition cord  72  of igniter  40  is connected to gas generator  66 . An ignition cord  74  of igniter  38  is connected to gas generator  60  of dual gas generator  22 . 
     Section  76  of tubular gas distributor  16  is connected to gas generator  78  of dual gas generator  22 . Section  80  of gas distributor  16  is connected to gas generator  82  of dual gas generator  26 . Section  84  of gas distributor  16  is connected to integrated thruster valve assembly  32 . An ignition cord  86  of igniter  42  is connected to gas generator  82  of dual gas generator  26 . An ignition cord  88  of igniter  38  is connected to gas generator  78  of dual gas generator  22 . A gas flow close/open valve  90  is located within section  80  of gas distributor  16 . 
     A section  92  of tubular gas distributor  18  is connected to gas generator  94  of dual gas generator  26 . A section  95  of gas distributor  18  is connected gas generator  96  of dual gas generator  20 . A section  98  of gas distributor  18  is connected to integrated thruster valve assembly  34 . A gas flow close/open valve  100  is connected within section  92  of gas distributor  18 . An ignition cord  89  of igniter  42  is connected to gas generator  94  of dual gas generator  26 . An ignition cord  102  of igniter  36  is connected to gas generator  96  of dual gas generator  20 . 
     In FIGURE, gas flow close/open valves  49 ,  70 ,  90  and  100  are closed. Igniters  36  and  38  are initially activated. These igniters cause the four gas generators  50 ,  96 ,  60  and  78 , in dual gas generators  20  and  22 , to be ignited. The ignited dual gas generators  20  and  22  produce hot gas. The hot gas from gas generator  50  passes through section  46  and through section  48  of gas distributor  12  and into integrated valve thrust assembly  28 . Hot gas from gas generator  60  passes through sections  58  and  68  of gas distributor  14  into integrated valve thrust assembly  30 . Hot gas from gas generator  78  passes through sections  76  and  84  of gas distributor  16  into integrated valve thrust assembly  32 . Hot gas from gas generator  96  passes through sections  95  and  98  of gas distributor  18  into integrated valve thrust assembly  34 . 
     The four gas generators  50 ,  60 ,  96  and  78  are activated during a first operational phase of the post boost control power assembly  6 . These four gas generators continue to burn, with gas pressure in the sections  46 ,  48 ,  58 ,  68 ,  76 ,  84 ,  95  and  98 , that are conducting gas, decreasing until the gas pressure decrease to a specified lower threshold pressure. 
     When this lower threshold gas pressure is reached, gas flow close/open valves  49 ,  70 ,  90  and  100  are opened, and igniters  40  and  42  are activated. Then, hot gas from gas generator  52  travels through section  44  of gas distributor  12 , through gas flow close/open valve  49 , and through section  48  of gas distributor  12 , into integrated valve thrust assembly  28 . Hot gas from gas generator  66  travels through section  62  of gas distributor  14 , through close/open valve  70 , through section  68  of gas distributor  14  and into integrated valve thrust assembly  30 . Hot gas from gas generation  82  passes through section  80 , through close/open valve  90  and section  84  of gas distributor  16 , into integrated valve assembly  32 . Hot gas from gas generator  94  passes through section  92 , through close/open valve  100 , through section  98  of gas distributor  18 , into integrated valve thrust assembly  34 . 
     The post boost control power assembly  6  of FIGURE provides hot gas to the four integrated valve thrust assemblies during two sequential time periods, each time period being greater than 340 seconds. The total boost control time period is greater than 680 seconds. The hot gas is produced by the controlled burning of any number of chemical compounds specifically designed for use in gas generators. The gas produced by burning such compounds is usually considered non toxic, non-corrosive and non-ablative. 
     A nozzle  120  of integrated valve assembly  28  is connected by a rigid hollow tube  122  to vent  123 . Vent  123  passes through body  10  of missile  8 . Similarly a nozzle  124  of integrated valve assembly  28  is connected by a rigid hollow tube  126  to a vent  127 . Vent  127  passes through body  10  of missile  8 . 
     When gas generator  50  is activated, gas flows from generator  50  through opened valves  160  and  162 , through nozzles  120  and  124 , through tubes  122  and  126 , and through vents  123  and  127 , when valve  49  is closed. When gas generator  52  is activated, and valve  49  is opened, gas flows from generator  52  through opened valves  160  and  162 , through nozzles  120  and  124 , through tubes  122  and  126 , and through vents  123  and  127 . 
     A nozzle  128  of integrated valve assembly  30  is connected by a rigid hollow tube  130  to vent  131 . Vent  131  passes through body  10  of missile  8 . Similarly a nozzle  132  of integrated valve assembly  30  is connected by a rigid hollow tube  134  to a vent  135 . Vent  135  passes through body  10  of missile  8 . 
     When gas generator  60  is activated and valve  70  is closed, gas flows from generator  60  through opened valves  164  and  166 , through nozzles  128  and  132 , through tubes  130  and  134 , and through vents  131  and  135 . When gas generator  66  is activated and valve  70  is opened, gas flows from generator  66  through opened valves  164  and  166 , through nozzles  128  and  132 , through tubes  130  and  134 , and through vents  131  and  135 . 
     A nozzle  136  of integrated valve assembly  32  is connected by a rigid hollow tube  138  to vent  139 . Vent  139  passes through body  10  of missile  8 . Similarly a nozzle  140  of integrated valve assembly  32  is connected by a rigid hollow tube  142  to a vent  143 . Vent  143  passes through body  10  of missile  8 . 
     When gas generator  78  is activated and valve  90  is closed, gas flows from generator  78  through opened valves  168  and  170 , through nozzles  136  and  140 , through tubes  138  and  142 , and through vents  139  and  143 . When gas generator  82  is activated and valve  90  is open, gas flows from generator  82  through opened valves  168  and  170 , through nozzles  136  and  140 , through tubes  138  and  142 , and through vents  139  and  143 , valve  90  being opened. 
     A nozzle  144  of integrated valve assembly  34  is connected by a rigid hollow tube  146 . Hollow tube  14  is connected to a vent  147 . Vent  147  passes through body  10  of missile  8 . Similarly a nozzle  148  of integrated valve assembly  34  is connected by a rigid hollow tube  150 . Hollow tube  150  is connected to a vent  151 . Vent  151  passes through body  10  of missile  8 . 
     When gas generator  96  is activated, gas flows from generator  96  through opened valves  172  and  174 , through nozzles  144  and  148 , through tubes  146  and  150 , and through vents  147  and  151 , valve  100  being closed. When gas generator  94  is activated, gas flows from generator  94  through opened valves  172  and  174 , through nozzles  144  and  148 , through tubes  146  and  150 , and through vents  147  and  151 , valve  100  being opened. 
     The teachings of U.S. Pat. No. 4,550,888, issued Nov. 5, 1985 are incorporated herein by reference. The integrated thruster valve assemblies  28 ,  30 ,  32  and  34  can be located outside of missile body  10 , as indicated in FIG. 1 of U.S. Pat. No. 4,550,888. 
     While the present invention has been disclosed in connection with the preferred embodiment thereof, it should be understood that there may be other embodiments which fall within the spirit and scope of the invention as defined by the following claims.