Abstract:
The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

Description:
FIELD OF THE INVENTION 
       [0001]    The present invention relates to thrust flow powered vehicles, such as missiles, jet skis or space vehicles. More particularly, but not exclusively, this invention concerns a thrust flow powered vehicle comprising a first thrust flow nozzle for expelling a first thrust flow in a first direction, and a second thrust flow nozzle for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction. The invention also concerns a method of operating a thrust flow powered vehicle and a thrust flow deflector for use as part of a thrust flow powered vehicle. 
       BACKGROUND ART 
       [0002]    One example of a prior art missile launch is where a missile is launched vertically, using a piston powered launch pad at a launch site. This is known as a “cold launch” as the missile motor is not used to launch the missile. Once the missile is in the air, it can be turned to be horizontal using lateral gas thrusters. However, if the missile motor fails the missile would fall (an inert descent situation) and would land on or near the launch site. An example of such a launch is described in US 2006/0107828. 
         [0003]    A second example of a prior art missile launch uses a similar missile to that of the first example. However, this second example missile has a rotatable thrust deflection device (called a “jetavator”) attached to a nozzle of a lateral gas thrusters. A representation of the jetavator  1  is shown in  FIG. 1 . The jetavator deflects some of the lateral flow from the nozzle  2  to provide an axial (longitudinal) component of thrust flow. The jetavator  1  is rotatable in relation to the nozzle  2 . This means that the missile rotates laterally to be horizontal (as before) but also moves axially (longitudinally). This moves the missile horizontally away from the launch site and is advantageous for safety and/or tactical reasons. Therefore, if the missile motor should fail, the missile would not fall and land on or near the launch site. It is also possible to have more than one jetavator, each jetavator deflecting lateral flow from a different nozzle. 
         [0004]    However, the control system required to control the rotation of the jetavator(s) to provide the required amount of axial thrust flow is complex. It is also necessary to provide sealing (shown by reference numeral  3  in  FIG. 1 ) to seal the jetavator over the nozzle. In addition, it is difficult to retrofit such a jetavator and control system to an existing missile due to requiring significant space and requiring a significant redesign. 
       DISCLOSURE OF THE INVENTION 
       [0005]    The present invention seeks to mitigate the above-mentioned problems. Alternatively or additionally, the present invention seeks to provide an improved thrust flow powered vehicle. 
         [0006]    The present invention provides, according to a first aspect, a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow outlet fairing associated with both the first and second thrust flow expellers, comprising a thrust flow deflector surface comprising a portion at an angle to the plane of the first and second directions, and an outlet portion through which an output thrust flow is to be expelled, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of the plane of the first and second directions. 
         [0007]    A thrust powered vehicle is intended to cover any moveable transport device that uses a thrust flow to move the device, which may or may not be able to accommodate passengers and/or cargo. For example, it may be a missile (that does not accommodate passengers, but may contain a cargo), a jet ski (that is intended to accommodate at least one passenger and not intended to transport cargo) or a spacecraft (that may or may not accommodate one or more passengers and/or cargo). 
         [0008]    Having a thrust flow outlet fairing over at least a portion of both the first and second thrust flow expellers allows a thrust flow deflector surface of the thrust flow outlet fairing to be at an angle to the plane of the first and second directions, and able to deflect at least a portion of both the first and second thrust flows to form the output thrust flow (with a component in the plane of the first and second directions, and a component out of the plane of the first and second directions) provided by the outlet portion. 
         [0009]    The amount of the different components, and therefore, the amount of thrust provided to the vehicle in the different directions, can be varied by changing the amounts and the relative amounts of flow coming out of each of the first and second thrust flow expellers. This means that there is no need for a separate control system, for example, for adjusting the angle of the thrust flow deflector surface. This makes the thrust flow powered vehicle potentially cheaper to make, more reliable, easier to maintain and/or lighter. 
         [0010]    The first and second directions are considered to be the average direction of the first and second flows, respectively. For example, flow expellers can expel flow in a range, generally a small range, of directions. However, here the average direction is meant. The invention is not concerned with simply expanding a flow (and therefore allowing the direction of parts of the flow to evenly expand to different directions, where the average direction of the flow does not change). 
         [0011]    Preferably, the first and second thrust flow expellers comprise nozzles. 
         [0012]    Preferably, the plane of the first and second directions is a lateral plane with respect to the vehicle and wherein the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows in an axial (longitudinal) direction with respect to the vehicle, such that the output thrust flow has both a lateral and an axial component with respect to the vehicle. This means that the first and second thrust flow expellers naturally provide a lateral thrust and the thrust flow deflector surface deflects this lateral thrust to also provide an axial thrust component. 
         [0013]    Preferably, the outlet portion comprises a single outlet for providing a single output thrust flow. 
         [0014]    Preferably, the outlet fairing is substantially in the shape of a wedge, with a short angled portion towards one end and a tapered portion towards an opposite end and wherein, preferably, the outlet portion is located on the short angled portion of the outlet fairing. This is an especially aerodynamic shape to make the vehicle more efficient. 
         [0015]    It is noted that the thrust flow deflector surface is a single surface that deflects at least a portion of both the first and second thrust flows. 
         [0016]    Preferably, the thrust flow deflector surface is fixed in position relative to the expellers. In other words the thrust flow deflector surface is not controllable to be rotated to affect the deflection of the thrust flows. This means that there is no control system for the thrust flow deflector surface, which makes the thrust flow powered vehicle potentially cheaper, more reliable, easier to maintain and/or lighter. 
         [0017]    Preferably, the thrust flow deflector surface is curved such that it extends from being in the plane of the first and second directions to being at an angle to the plane of the first and second directions. This means that the deflection is a gradual deflection, resulting in an aerodynamically efficient arrangement, with minimal drag and flow turbulence. 
         [0018]    Preferably, the thrust flow deflector surface has a maximum angle of between 5 and 30 degrees to the plane of the first and second directions. This provides adequate axial thrust whilst still providing an aerodynamically efficient arrangement. 
         [0019]    Preferably, the thrust flow powered vehicle further comprises a tubular extension on the outlet portion, and wherein, preferably, the thrust flow deflector surface has a maximum angle of over 10 degrees to the plane of the first and second directions. The tubular extension is for extending the length over which deflection of the thrust flows takes place. Having a tubular extension minimises the drag and flow turbulence of the arrangement and is particularly advantageous when the maximum angle of the deflector surface is over 10 degrees. 
         [0020]    More preferably, the tubular extension has a length similar to the diameter of the first thrust flow expeller and/or the second thrust flow expeller. This provides an especially efficient arrangement, which minimises the shock waves caused by the deflected flow. 
         [0021]    Preferably, the first direction is substantially orthogonal to the second direction. This gives maximum flexibility in the control of the direction, especially the lateral direction, of the vehicle. 
         [0022]    Preferably, the first thrust flow to be expelled by the first thrust flow expeller and the second thrust flow to be expelled by the second thrust flow expeller are independently controllable. 
         [0023]    Preferably, the vehicle is a missile, jet ski or a space vehicle. More preferably the vehicle is a missile. Even more preferably, the vehicle is a missile for use in a cold launch system. In other words, the missile motor is not used to launch the missile and instead the missile is launched by an external, for example, a piston powered launch pad at a launch site. 
         [0024]    According to a second aspect of the invention there is also provided a method of operating a thrust flow powered vehicle, the method comprising the steps of expelling a first thrust flow in a first direction from a first expeller of the vehicle, expelling a second thrust flow in a second direction from a second expeller of the vehicle, the second direction being a different direction to the first direction but sharing a plane with the first direction, and using a deflector over at least a portion of both the first and second expellers to deflect at least a portion of both the first thrust flow and the second thrust flow to provide an output thrust flow with both a lateral and an axial component relative to the vehicle, thereby moving the vehicle in a lateral and an axial direction. 
         [0025]    Preferably, the first thrust flow expelled and the second thrust flow expelled are controlled independently. 
         [0026]    According to a third aspect of the invention there is also provided a thrust flow deflector for use as part of a thrust flow powered vehicle, the deflector comprising an inlet portion for receiving a first inlet thrust flow in a first direction, and a second inlet thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, an outlet portion for providing an output thrust flow, and a thrust flow deflector element in between the inlet portion and the outlet portion, for deflecting at least a portion of both the first and second inlet thrust flows to form the output thrust flow, the deflector element having a deflector surface at an angle to the plane of the first and second directions, such that, in use, there is provided an output thrust flow with a component in the plane of the first and second directions, and a component out of the plane of the first and second directions. 
         [0027]    It is possible to retrofit such a thrust flow deflector to an existing thrust flow powered vehicle that has a twin expeller arrangement. The thrust flow deflector may be attached across the exit plane of the twin expellers. 
         [0028]    It will of course be appreciated that features described in relation to one aspect of the present invention may be incorporated into other aspects of the present invention. For example, the method of the invention may incorporate any of the features described with reference to the apparatus of the invention and vice versa. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0029]    Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which: 
           [0030]      FIG. 1  shows a side view of a jetavator according to the prior art; 
           [0031]      FIG. 2  shows a cutaway side view of part of a missile according to a first embodiment of the invention; 
           [0032]      FIG. 3  shows an enlarged view of part of a missile according to a second embodiment of the invention; 
           [0033]      FIG. 4  shows a plan view of an outlet fairing for use on the missile of  FIG. 2  or  FIG. 3 ; and 
           [0034]      FIG. 5  shows the outlet fairing of  FIG. 4  mounted on part of a missile according to a third embodiment of the invention; 
           [0035]      FIG. 6  shows a plan view of a different outlet fairing for use on the missile of  FIG. 2, 3 or 5 ; and 
           [0036]      FIG. 7  shows the outlet fairing of  FIG. 6  mounted on part of a missile according to a fourth embodiment of the invention. 
       
    
    
     DETAILED DESCRIPTION 
       [0037]      FIG. 2  shows a cutaway side view of part of a missile  10  according to a first embodiment of the invention. In this part of the missile  10 , there is a control system  11  for the missile and a gas generator  12 . The gas generator is used to provide high pressure propellant to be expelled from the missile  10 . The propellant is expelled at a speed of approximately Mach 3. 
         [0038]    The propellant is expelled via expansion cone nozzles (first nozzle shown as reference numeral  30 ). It is to be noted that there is also a second nozzle (not shown) adjacent to the first nozzle  30  and orthogonal to it. The first nozzle  30  expels propellant downward (as shown on the page), whereas the second nozzle is behind the first nozzle and expels propellant outwards (i.e. out of the page). Hence, the propellant flow out of both nozzles is in a shared lateral plane, this lateral plane extending in and out of the page along a line going through the central axis of the first nozzle  30  shown. Other than the orientation and position of the first and second nozzles, they are identical. 
         [0039]    Each nozzle has an associated piston (the piston of the first nozzle  30  is shown as reference numeral  32 ) behind the nozzle to control the expelling of the high pressure propellant. Each piston has an associated piston controller located behind the piston (the piston controller of the first nozzle  30  is shown as reference numeral  34 ). 
         [0040]    Attached to the side of the missile  10  immediately in front of the nozzles is an outlet fairing  20 . The outlet fairing is made of titanium. The outlet fairing is a wedge shape with a long shallow angled side  21  and a short high-angled end portion  22 . The long shallow side  21  is at an angle  23  to the rest of the side of the missile. This angle  23  is 15 degrees. 
         [0041]    It is noted that the outlet fairing  20  is typically subjected to propellant temperatures in excess of 2000 degrees Kelvin and the outside of the fairing  20  is typically subjected to “aero heating” of approximately 500 degrees Kelvin. The outlet fairing  20  is designed to be aerodynamic. 
         [0042]    Between the outlet ends of the nozzles and the short high-angled end portion  22  is a curved flow deflector surface  24  that deflects the flow from both first  30  and second nozzles. This flow deflector surface  24  deflects the flow out of the lateral plane to have an axial (longitudinal) component (i.e. a component that is horizontal on the page). It can be seen that it continues the expansion of the expansion cone nozzles but at an angle to the lateral plane. 
         [0043]    The resultant deflected flow is expelled from the outlet fairing at an angle  25  to the side of the missile. This angle  25  is 60 degrees. In other words, the propellant has been deflected 30 degrees from the lateral plane. 
         [0044]    As the propellant is expelled at Mach 3, the deflection at angles of more than 15 degrees (here it is 30 degrees) causes significant losses due to shock waves forming. Hence a short tubular extension  29  is used. This short tubular extension  29  has a length corresponding to the diameter of the outlet (expanded) end of the first and second nozzles. 
         [0045]      FIG. 3  shows an enlarged view of part of a missile  100  according to a second embodiment of the invention. This second embodiment is similar to the first embodiment. Here, there are shown two orthogonal expansion cone nozzles in a shared lateral plane; first nozzle  130  and second nozzle  131 . 
         [0046]    Also, shown is a flow deflector surface  124  for deflecting the two orthogonal propellant flows from the first  130  and second  131  nozzles. The flow deflector surface  124  deflects the propellant flow to have an axial component. 
         [0047]      FIG. 4  shows a plan view of an outlet fairing  20  for use on the missile of  FIG. 2  (missile  10 ) or  FIG. 3  (missile  100 ). Here, the wedge shape of the faring can be seen clearly, with long shallow side  21  and short high-angles end portion  22 . 
         [0048]    The outlet fairing  20  also comprises two side fixing points  26 ,  27  for attaching the outlet fairing to a side of the missile  10 ,  100 . These fixing points are sunken holes in the sides of the fairing  20  for accommodating bolts. There is also provided sealant (not shown) around the outlet fairing  20  to prevent leakage or blowback. 
         [0049]    In the high-angled end portion  22  is a flow deflector surface  24  leading to an outlet  28 . Here, the two orthogonal nozzles  130 ,  131  can be seen expelling propellant towards the flow deflector surface  24 . 
         [0050]      FIG. 5  shows the outlet fairing  20  of  FIG. 4  mounted on part of a missile  200  according to a third embodiment of the invention. This third embodiment is similar to the first and second embodiments. The missile comprises two pairs of nozzles; a first pair  230 ,  231  being shown without a fairing in place over them and a second pair that are covered by the outlet fairing  20 . 
         [0051]    Here, at a lower portion of the figure, two orthogonal expansion cone nozzles  230 ,  231  can be seen, arranged to expel propellant in a lateral plane. The outlet fairing  20  has been removed from the figure to allow the position and orientation of the nozzles  230 ,  231  to be seen. A hatch  213  adjacent to the nozzles  230 ,  231  provides access to the inside of the outlet fairing  20  when it is attached to the missile  200 . 
         [0052]    At an upper portion of the figure, an outlet fairing  20  can be seen. The outlet fairing  20  is attached over two nozzles (not seen clearly in the figure). These nozzles are similar to nozzles  230 ,  231 . The long shallow side  21  and high-angled end portion  22  of the fairing  20  can be seen. Also, the fixing point  26  on one side of the outlet fairing  20  is also shown. 
         [0053]      FIG. 6  shows a plan view of an outlet fairing  120  for use on the missile of  FIG. 2  (missile  10 ),  FIG. 3  (missile  100 ) or  FIG. 5  (missile  200 ). Here, the fairing  120  is a triangular wedge shape, with long shallow side  121  and short high-angles end portion  122 . 
         [0054]    The outlet fairing  120  also comprises two side fixing points  126   a,    126   b  and an end fixing point  127  for attaching the outlet fairing to a side of the missile  10 ,  100 ,  200 . These fixing points are sunken holes in the fairing  120  for accommodating bolts. There is also provided sealant (not shown) around the outlet fairing  120  to prevent leakage or blowback. 
         [0055]    In the high-angled end portion  122  is a flow deflector surface  124  leading to an outlet  128 . Here, the two orthogonal nozzles  130 ,  131  can be seen expelling propellant towards the flow deflector surface  124 . 
         [0056]      FIG. 7  shows the outlet fairing  120  of  FIG. 6  mounted on part of a missile  300  according to a fourth embodiment of the invention. This fourth embodiment is similar to the first, second and third embodiments. 
         [0057]    Here, at a lower portion of the figure, two orthogonal expansion cone nozzles  330 ,  331  can be seen, arranged to expel propellant in a lateral plane. The outlet fairing  120  has been removed from the figure to allow the position and orientation of the nozzles  330 ,  331  to be seen. 
         [0058]    At an upper portion of the figure, an outlet fairing  120  can be seen. The outlet fairing  120  is attached over two nozzles (not seen clearly in the figure). These nozzles are similar to nozzles  330 ,  331 . The long shallow side  121  and high-angled end portion  122  of the fairing  120  can be seen. Also, the fixing points  126   a,    126   b  and  127  on the outlet fairing  120  are also shown. 
         [0059]    In use of all of the above embodiments, an outlet fairing  20 ,  120  is fixed to a missile ( 10 ,  100 ,  200  or  300 ) by fixing points  26  (a and b),  27  and sealant (not shown) is applied around the outlet fairing  20 ,  120 . After the missile  10 ,  100 ,  200 ,  300  is cold launched vertically from a launch site, gas generated in gas generator  12  is expelled using the piston nozzles  32 , through the nozzles  30 ,  130 ,  131 ,  230 ,  231 ,  330 ,  331  in a lateral plane of the missile  10 ,  100 ,  200 ,  300 . This lateral flow component provides lateral thrust to turn the missile  10 ,  100 ,  200 ,  300  from a vertical orientation to a horizontal orientation. 
         [0060]    This propellant is deflected by the flow deflector surface  24 ,  124  of the outlet fairing  20 ,  120  to also have an axial component. In other words, the propellant is deflected to have a component parallel to the axis of the missile  10 ,  100 ,  200 ,  300 . This means that thrust is provided in the axial direction which propels the missile  10 ,  100 ,  200 ,  300  forwards and moves it away (in a horizontal sense) from the launch site. Hence, if the main missile motor is not ignited properly, the missile  10 ,  100 ,  200 ,  300  will not fall back down near to the launch site. 
         [0061]    The amount of lateral and axial thrust provided by the propellant to the missile  10 ,  100 ,  200 ,  300  is controlled by the control system  11  and piston controllers  34  by controlling the amount of propellant expelled from each of the nozzles  30 ,  130 ,  131 ,  230 ,  231 ,  330 ,  331 . This variable flow expelled from the nozzles allows a variable resultant force to be achieved that can be varied through 90 degrees laterally and up to 30 degrees axially (longitudinally). Using the control system  11  and piston controllers  34  to control the amount of axial thrust means there is no need for a separate control system to control the rotation of the nozzles  30 ,  130 ,  131 ,  230 ,  231 ,  330 ,  331 . In addition, it is possible to retrofit such a fairing  20 ,  120  to any existing missile with a twin expeller arrangement. 
         [0062]    Whilst the present invention has been described and illustrated with reference to particular embodiments, it will be appreciated by those of ordinary skill in the art that the invention lends itself to many different variations not specifically illustrated herein. By way of example only, certain possible variations will now be described. 
         [0063]    Instead of having nozzles  30 ,  130 ,  131 ,  230 ,  231 ,  330 ,  331 , any of the embodiments of the invention may employ jet pipes for expelling the propellant from the missile. 
         [0064]    The fairings  20 ,  120  in any of the embodiments may be made from steel, instead of titanium. In addition, the fairings  20 ,  120  in any of the embodiments may be coated with a thermal barrier such as Zirconia, especially if they are designed for long duration use. As a further alternative, the fairings  20 ,  120  in any of the embodiments may be made from composites or plastics, especially if a cold propellant was used. 
         [0065]    In the above described embodiments, the flow deflector surface  24 ,  124  is fixed. However, as an alternative, the outlet could be an actuated device, for example a rotating device, to vary the angle of the output flow with respect to the axial (longitudinal) direction. The outlet could be a combination of a fixed fairing and an actuated device. The actuated device may be hinged at the nozzle exit plane and may comprise gas passageways passing through a rotatable ball joint. 
         [0066]    In the above described embodiments, the flow deflector surface  24 ,  124  is at an angle of 30 degrees. However, it could be at any angle up to 30 degrees. Angles over 30 degrees could be used but these are not considered to be likely as at above 30 degrees the losses experienced begin to significantly reduce performance of the missile. 
         [0067]    Where in the foregoing description, integers or elements are mentioned which have known, obvious or foreseeable equivalents, then such equivalents are herein incorporated as if individually set forth. Reference should be made to the claims for determining the true scope of the present invention, which should be construed so as to encompass any such equivalents. It will also be appreciated by the reader that integers or features of the invention that are described as preferable, advantageous, convenient or the like are optional and do not limit the scope of the independent claims. Moreover, it is to be understood that such optional integers or features, whilst of possible benefit in some embodiments of the invention, may not be desirable, and may therefore be absent, in other embodiments.