METHOD AND APPARATUS FOR ARTIFICIAL DISTRIBUTION OF INSECTS OR SPRAY

Abstract

A diffuser for distributing spray or insects from an aircraft is mounted on an aircraft and comprises a distribution tube connected to an insect source at a first end and open to the outside at a second end for distribution of the insects. A nozzle surrounds the second end and a tube cover surrounds the second end within the nozzle. The tube cover has an aerofoil, or wing-shaped, cross section. The nozzle shape sets up an air transition volume between the aircraft and ambient air designed for a maximum wind shear over any cubic centimeter volume within the air transition volume to be less than 60 km/h, and therefore allowing distribution of insects such as mosquitoes from the aircraft without damage, or allowing aerosols to be spread as large droplets.

Claims

1. A diffuser for distributing material from an aircraft, the diffuser being mounted on an aircraft and comprising: at least one distribution tube connected to a source at a first end and open to the outside at a second end for distribution of the material; a nozzle surrounding the second end; and a tube cover surrounding the second end within the nozzle, the tube cover having an aerofoil-shaped cross section.

2. The diffuser of claim 1, wherein the nozzle comprises a subsonic two-dimensional converging-diverging nozzle.

3. The diffuser of claim 2, wherein the nozzle comprises a bi-cubic polynomial internal contour.

4. The diffuser of any of claims 1 to 3, wherein the nozzle comprises an elliptical external shape.

5. The diffuser of any one of the preceding claims, wherein the aerofoil shape is an NACA standard shape.

6. The diffuser of claim 5, wherein the NACA standard shape is an NACA 0018 standard shape.

7. The diffuser of claim 5, wherein the tube cover is positioned within the nozzle such that a smooth external contour of the standard shape limits flow separation to the near wake of the blunt trailing edge section of the nozzle.

8. The diffuser of any one of the preceding claims, wherein the source is provided with an overpressure.

9. The diffuser of claim 8, wherein the overpressure is such as to provide an air velocity exiting the tube at the second end of substantially 1 m/s (one meter per second).

10. The diffuser of any one of the preceding claims, wherein the nozzle is cubic.

11. The diffuser of claim 10, wherein the source is provided with an overpressure and the overpressure is such as to provide an air velocity exiting the tube at the second end of substantially 1 m/s.

12. The diffuser of any one of the preceding claims, wherein the material being distributed comprises insects.

13. The diffuser of claim 12, wherein the insects being distributed comprise relatively fragile insects being unable to bear a wind shear in excess of 60 km/h.

14. The diffuser of claim 12, wherein the insects being distributed comprise male insects.

15. The diffuser of claim 14, wherein the insects being distributed comprise sterile male mosquitoes.

16. A diffuser for distributing material from an aircraft, the diffuser being mounted on an aircraft and comprising: at least one distribution tube having an opening providing air at a speed of at least 1 m/s; a nozzle surrounding the opening; and a tube cover surrounding the second end within the nozzle, the tube cover having a wing-shaped cross section.

17. The diffuser of claim 1, wherein said material comprises insects.

18. The diffuser of claim 17, wherein said insects are mosquitoes.

19. An air transition volume between an aircraft flying in excess of stall speed and ambient air, the transition region comprising: a first volume immediately behind an opening of a tube, shielded by a wing-shaped tube cover and surrounded by a nozzle, defined by an airspeed of air exiting the opening at a velocity of at least 1 m/s less than a speed of the aircraft; successive volumes receding from the first area of successively reduced speeds, eventually merging into the ambient air, the transition volume being characterized by a maximum wind shear over any cubic centimeter volume within the air transition volume being less than 60 km/h.

20. A method of distributing insects from an aircraft, comprising: setting up an air transition volume between a speed of the aircraft and a speed of ambient air, the aircraft flying in excess of a respective aircraft stall speed, the air transition volume being such that a maximum wind shear over any cubic centimeter volume within the air transition volume is less than 60 km/h; using overpressure to push insects out of an insect source into a tube; terminating the tube outside the aircraft into the air transition volume; and allowing the insects to exit the tube into the air transition volume.

21. A method of distributing insects from an aircraft, comprising: pushing insects out of an insect source into a tube; terminating the tube at an opening outside the aircraft; and using overpressure in the tube to expel the insects from the opening.

22. A diffuser for distributing insects from an aircraft, the diffuser being mounted on an aircraft and comprising: at least one distribution tube connected to an insect source at a first end and open to the outside at a second end for distribution of the insects; and a nozzle surrounding the second end.

Description

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

[0056] Some embodiments of the invention are herein described, by way of example only, with reference to the accompanying drawings. With specific reference now to the drawings in detail, it is stressed that the particulars shown are by way of example and for purposes of illustrative discussion of embodiments of the invention. In this regard, the description taken with the drawings makes apparent to those skilled in the art how embodiments of the invention may be practiced.

[0057] In the drawings:

[0058] FIG. 1 is a simplified illustration of the contours of a bi-cubic nozzle for insect distribution according to a first embodiment of the present invention;

[0059] FIG. 2 is a simplified diagram showing the aerofoil shape of the tube cover according to an embodiment of the present invention;

[0060] FIG. 3 is a simplified diagram showing simulated air velocities resulting from the aerofoil shape of FIG. 2;

[0061] FIG. 4 is a simplified diagram a substantially linear nozzle shape according to an embodiment of the present invention;

[0062] FIG. 5 is a simplified diagram showing simulated air velocities resulting from the nozzle shape of FIG. 4;

[0063] FIG. 6 is a simplified diagram showing a bi-cubic nozzle shape according to an embodiment of the present invention;

[0064] FIG. 7 is a simplified diagram showing simulated air velocities resulting from the nozzle shape of FIG. 6;

[0065] FIG. 8 is a simplified diagram showing simulated air velocities using a wide cubic nozzle shape according to an embodiment of the present invention;

[0066] FIG. 9 is a simplified diagram showing another bi-cubic nozzle according to an embodiment of the present invention, with an extended exit area;

[0067] FIG. 10 is simplified diagram showing simulated air velocities resulting from the nozzle shape of FIG. 9;

[0068] FIG. 11 simplified diagram showing simulated air velocities resulting from the nozzle shape of FIG. 9 when air exits the insect delivery tube at a velocity of around 1 m/s;

[0069] FIG. 12 is a simplified diagram showing air flow velocities resulting from the nozzle shape of FIG. 1 when air exits the insect delivery tube at a velocity of around 1 m/s;

[0070] FIG. 13 is a simplified diagram showing air flow velocities resulting from a variation of the nozzle shape of FIG. 1 wherein the throat of the nozzle is widened, and when air exits the insect delivery tube at a velocity of around 1 m/s; and

[0071] FIG. 14 is a simplified diagram and cross-section of the dispenser of the present invention attached to an aircraft wing.

DESCRIPTION OF SPECIFIC EMBODIMENTS OF THE INVENTION

[0072] The present invention, in some embodiments thereof, relates to a method and apparatus for artificial distribution of material such as insects and, more particularly, but not exclusively, to the distribution of insects as part of disease control programs, pollination programs and the like, or to distribution of sprays in general.

[0073] A diffuser for distributing material from an aircraft, is mounted on an aircraft and comprises a distribution tube connected to an insect source at a first end and open to the outside at a second end for distribution of the insects. A nozzle surrounds the second end and a tube cover surrounds the second end within the nozzle, the tube cover having an aerofoil, or wing-shaped, cross section. The nozzle shape and aerofoil combination sets up an air transition volume between the aircraft and ambient air and within the transition volume there is a maximum wind shear over any cubic centimeter volume which is less than 60 km/h and between 36 and 54 km/h, for an airplane speed of ˜120 km/hr, therefore allowing distribution of the material from the aircraft without damage.

[0074] Herein the term “aircraft” refers to any airborne craft and includes conventional aeroplanes, as well as unmanned aerial vehicles, helicopters, gliders, and lighter-than-air craft.

[0075] Herein the term diffuser is used to mean an attachment or duct for broadening an airflow and reducing its speed. The material, for example mosquitoes, is injected into the diffuser for safe distribution.

[0076] As discussed in the background, mosquitoes are a particularly fragile kind of insect which cannot be distributed by conventional air dispersion. The transition volume allows mosquitoes to be safely distributed.

[0077] In an alternative embodiment, the material may be a spray. Different sprays have different ideal droplet sizes. A phenomenon with aerial spraying is that the sudden transition to high windspeed causes a small drop size, so that aerial spraying with a large drop size has hitherto been a technical challenge. The present embodiments, which provide a transition air volume, cushion the spray from a sudden exposure to a high wind velocity and thus allow a relatively large droplet size with aerial delivery. Before explaining at least one embodiment of the invention in detail, it is to be understood that the invention is not necessarily limited in its application to the details of construction and the arrangement of the components and/or methods set forth in the following description and/or illustrated in the drawings and/or the Examples. The invention is capable of other embodiments or of being practiced or carried out in various ways.

[0078] Referring now to the drawings, FIG. 1 illustrates a diffuser 10 for distributing insects from an aircraft. The diffuser may be mounted on an aircraft, in particular under and slightly behind an aircraft wing as shown in FIG. 12 hereinbelow. The diffuser comprises one or more distribution tubes 12 which are connected to an insect source at a first end (not shown) typically within the aircraft and open to the outside at a second end 14 for distribution of the insects.

[0079] A nozzle 100 surrounds the end of the tube, and a tube cover 102 surrounds the second end inside the nozzle. The tube cover has an aerofoil or wing-shaped cross section.

[0080] Nozzle 100 may be a subsonic two-dimensional converging-diverging nozzle, and may comprise a bi-cubic polynomial internal contour.

[0081] The nozzle 100 may further comprise an elliptical external shape. The nozzle may be elongated to extend along the length of the wing, as shown in FIG. 12, so as to cater for multiple outlet tubes 12. Alternatively, the nozzle can be round and cater for a single tube 12.

[0082] The wing or aerofoil shape may be an NACA standard shape, for example the NACA 0018 standard shape.

[0083] The tube cover 102 is positioned within the nozzle at a location selected such that the smooth external contour of the standard shape limits flow separation that would otherwise occur in such a nozzle to the near wake of the blunt trailing edge section 16 of the nozzle.

[0084] The insect source may be provided with an overpressure, so as to provide an air velocity exiting the tube of substantially 1 m/s. The nozzle 100 may use a range of cubic shapes for its internal surface, as will be discussed below, and is not limited to the bi-cubic shape shown.

[0085] The insects may comprise relatively fragile insects where fragile is defined as being unable bear a wind shear in excess of 60 km/h and more particularly in the range of 36-54 km/h. In particular, experimental results show that releasing into an airspeed of 10-15 m/s does not kill the mosquitoes. This is equivalent to 36-54 km/hr. Once outside the airspeed gradually falls until reaching the same speed as the outside air.

[0086] The expectation is that most of the insects will survive. The diffuser is not limited to distribution of fragile insects, although it is designed to cater for fragile insects. Any insects may usefully be distributed thereby as desired. The insects being distributed may be any insects but the diffuser is particularly useful for distribution of male insects engineered for disease vector eradication programs, for example, sterile male mosquitoes or genetically modified mosquitoes.

[0087] In addition to insects, the nozzles of the present embodiments may be used for sprays, as mentioned.

[0088] The nozzle may set up an air transition volume between the aircraft flying in excess of stall speed and ambient air. An air transition volume is shown for example in FIG. 11 hereinbelow. The air transition volume may ensure a relatively gradual transition between the two air speeds, namely of the aircraft and the ambient air, which allows even relatively fragile insects to survive the distribution operation. A first volume of the air immediately behind an opening of the distribution tube 12 is shielded by the aerofoil, or wing-shaped, tube cover 102 and surrounded by nozzle 100 as explained. The transition volume has a first part, immediately behind the tube opening, which is defined by an airspeed of air exiting the opening at a velocity of about 1 m/s less than the aircraft speed. That is to say, given that the aircraft is moving and the air is assumed to be static, then the 1 m/s ejection speed is a reduction in speed. Then successive volumes of the air receding backwards and radially outwardly from the first area, have successively reduced speeds, eventually merging into the ambient air. The gradual transition may be characterized by a maximum wind shear experienced by the mosquitoes as they are expelled into the air transition volume being less than 60 km/h and in an example less than 25 km/h.

[0089] Thus the insects may be distributed from the aircraft by setting up the air transition volume as described above, using overpressure to push insects out of an insect source into tube 12, terminating the tube outside the aircraft into the air transition volume, and allowing the insects to exit the tube into the air transition volume.

[0090] As mentioned above, the air transition volume is also useful in the case of sprays, as sudden exposure to a large air speed has the effect of breaking up droplets. The air transition volume by contrast allows for larger droplets.

[0091] Larger droplets equate with less drift, so that the droplets fall closer to their release points. This is particularly important with toxic materials, with expensive materials, and with farmers whose neighbors might be using organic methods, and also reduces waste. Also a larger droplet covers the plant or ground on which it lands with more material.

[0092] Considered in greater detail there is provided a device to release mosquitoes and like fragile insects from an aircraft using a diffuser/pod like configuration with openings on both sides and an injection unit within.

[0093] The flow within the 2D diffuser may be controlled by its geometry, dimensions and location, which together act as a controller for the flow along the diffuser and prevent flow separation. Additional control may be provided by blowing air outside of the inner element, that is through the cover tubes.

[0094] In order to prevent the impact of air velocity on the insects during their release from the airplane, the present embodiments may lower the exit velocity difference compared to the immediately surrounding air, and have the actual velocity of the insects gradually increase prior to exposure to the environmental air surrounding the aircraft.

[0095] More specifically, while the airplane is flying at a speed greater than 110 km/hr, the embodiments allow the mosquitoes to experience only some 25-60 km/hr wind shear during their exit, and to gradually be introduced to the stationary surrounding air.

[0096] The idea is that at no point during the transition should the insects experience anything more than the 25-60 km/hr wind shear, thus allowing for safe and effective distribution from the air without damage. A preferred initial air speed within the volume is around 10 m/s which is 36 km/hr, and afterwards, the flow gradually increases. It is noted that the above speeds are correct for an aircraft travelling at 120 km/h, which is typical for a small agricultural plane. If the aircraft were to fly faster than the wind shear would increase, which may still be useful for applications such as distribution of fruit flies or for chemical spraying. If used for chemical spraying then atomizers may be added. Also if the diffuser is to be used with larger aircraft having higher stall speeds then the geometry of the diffuser may be modified accordingly.

[0097] Diffusers as such are well known and exist in the market for many applications, although they have never been used or suggested for distributing insects. At the exit of a diffuser, the velocity is lower than at the entrance, however, if needed to further decrease the velocity two options exist: [0098] Increasing the length of the diffuser. This is not possible in the present case since it would lead to a length which is too large, a big, heavy system causing considerable drag to the airplane. The result would be expensive, in particular requiring the use of a large plane. [0099] If keeping to the same dimensions, it is possible to increase the angle of curvature, thus increasing the area and particularly the height between the upper and lower diffuser tips. However if the angle of curvature is more than 6-7 degrees, then flow separation starts to appear—the speed slows as the area increases, and airflow trying to move from the low pressure area to the high pressure area starts to separate. This effect may cause harm to the fragile insects.

[0100] The present embodiments may solve the wind speed problem by managing the airflow using an additional element, hereinafter referred to as a tube cover, within the diffuser.

[0101] The tube cover 102 may actually control the vertical extent of the region of slow moving air around the exit of the diffuser, and thus prevent flow separation. The use of the tube cover 102 thus provides a small dimension element, but with low exit velocity. With the tube cover alone, the velocity at the exit is very small which is helpful for the just released insects, but the area within which the velocity is low is in itself very small, and essentially defined by the height of the tube cover.

[0102] Now the role of the diffuser together with the tube cover is to increase the region of the low velocity, and in particular its length, thus allowing the air velocity to gradually increase towards a match with the surrounding air.

[0103] Conventionally, for applications using diffusers, the design goal is to provide a flow which is as uniform as possible. Putting the tube cover inside prevents the flow from being uniform. In the present case, the goal is a velocity difference from the exit point to the ambient air which is low enough at all points for releasing of insects, so the uniformity of the flow is less important.

[0104] The present embodiments may thus provide control of the airflow and prevent separation of airflow regions inside a small dimension 2D diffuser with a curvature of more than 6-7 degrees, by introducing a central element which can control the flow along the diffuser sides.

[0105] Parameters associated with the tube cover are: [0106] 1. Location inside the diffuser [0107] 2. Dimensions [0108] 3. Geometry [0109] 4. Internal velocity of airflow exiting the diffuser and carrying the insects. The blown air eliminates some undesirable effects, as discussed in greater detail below, and can help achieve a more uniform flow within the device.

[0110] In contrast with the prior art chilled release box, the present embodiments push out the insects with air blow and positive air pressure, rather than suck out the insects with negative pressure.

[0111] The present embodiments may provide a small dimension diffuser with no flow separation, creating a volume with gradual velocity differences, such that velocity gradually increases at the exit point until it matches the external air flow. The result is the release of fragile insects at low relative air velocity.

[0112] As mentioned, the present embodiments relate to the search for a safe and efficient method to control vector-borne diseases, specifically Dengue fever and Malaria, over sizeable regions, including urban area. The preferred method is to use engineered sterile male mosquito to mate preferentially with females and disrupt fertility, thus disrupting continuity of the Anopheles, Aedes Aegypti and other types of mosquitoes which are the carriers of the disease.

[0113] In order to achieve fast and even cover over large areas, including places that are hard to get to, aerial operation is suggested, as discussed above. The general idea is to propose a sub-system that is as close as possible to existing aerial crop dusting techniques so as to work on the same equipment with minimal conversion.

[0114] The presently provided mosquito delivery sub-system (MDSS) embodiments may be fitted to typical agricultural crop-dusting aircraft. In particular, the present study used the Brazilian, Embraer EMB-202 Ipanema agricultural aircraft with standard petrol engine as the ‘test-bed’. Generally, agricultural aircraft come in low wing and high wing variants, and the geometry of the present embodiments may be modified so that for aircraft with high-wing, an axi-symmetric version of the diffuser is provided.

[0115] The presently described approach may use storage containers stored inside the fuselage of the aircraft. The containers may be kept at slight over-pressure. The MDSS (mosquito delivery sub-system) may conveniently be attached to the aircraft beneath and slightly beyond the wing. The delivery ports are evenly distributed along the span of the MDSS.

[0116] A design objective of the MDSS is to minimize the added drag to the aircraft, as well as to ensure comfortable initial conditions for the mosquitoes during delivery.

[0117] In the following, it is assumed that the working flight speed, which should be as high as possible, can be taken to be nominally 20% higher that the stall-speed of the aircraft.

[0118] In the following it is further assumed that the mosquitoes require to be released into a relatively low speed air environment of the order of 10 m/s.

[0119] As previously mentioned, the storage containers are located in the fuselage, and tubes or chutes allow a smooth transfer of the mosquitoes from the storage tanks to the tube outlets at particular delivery spots. The Tubes are packaged together within an elongated nozzle and covered by an aerodynamic smooth cover, which may for example be similar to a standard NACA-0018 airfoil section. Each one of the tubes ends at a specific delivery port. The smooth contoured cover, denoted herein as the tube-cover, is embraced by two nozzle segments, upper and lower, of a subsonic diffuser. Part of the flight airstream enters the diffuser. The local velocity of the air inside the diffuser increases through the converging part of the diffuser, and reaches a maximum at the throat. Further downstream, the local velocity decreases as the segments diverge and the height of the diffuser increases. Into the low velocity region the mosquitoes are released with a small ejection velocity V.sub.eject of the order of V.sub.eject˜1.0 [m/s]. The specific delivery point is in the shadow or wake of the Tube Cover. In the immediate neighborhood of the mosquito delivery point, local air velocities are lower than V=10÷15 [m/s]. In other words there are regions that enables safe exit of the mosquitoes.

[0120] The main geometrical parameters controlling the low speed air and its extent have been defined as: [0121] 1) The overall diffuser length [0122] 2) The diffuser throat height [0123] 3) The diffuser exit height [0124] 4) Functional shape of the diffuser inner contours [0125] 5) Relative location of the tube cover inside the diffuser.

[0126] A mathematical analysis has been based on high fidelity solutions of two-dimensional (2D), incompressible air flow around a delivery mechanism that is attached to the wing of agricultural airplanes. The numerical simulations use the full Reynolds Averaged Navier-Stokes (RANS) system of equations with two equation (k−ε) turbulence model. The solution uses finite volume discretization and the algorithm is second order.

[0127] Within the above mentioned design parameters, the shape of the “mosquito delivery sub-system” (MDSS) was optimized requiring a blend of: a) maximum size of low speed area, b) minimum MDSS drag.

[0128] A preferred MDSS configuration is presented in FIG. 1. As discussed above, FIG. 1 shows a subsonic two-dimensional converging-diverging nozzle 100 with a bi-cubic polynomial internal contour and a slightly modified elliptical external shape.

[0129] Tube cover 102 has a wing-shaped cross section as discussed above and shields the pipes from which the mosquitoes are released. The nozzle has a region 104 of reducing cross-section and increasing air velocity, a throat 106 and a region 108 downstream of the throat of steadily increasing cross-section and reduced air velocity.

[0130] As far as the present inventors are aware, the embodiments provide a novel approaches in several aspects. First, in dealing with live mosquitoes, flow conditions may be constrained in ways that are not well defined, in the sense that requirements like “suitable flow conditions for mosquitoes” do not specify the extent of the low speed region, nor do they define permissible velocity gradients. Second, it is well known that subsonic flow is decelerated by increasing nozzle cross section. However, if the diffuser's area increases too fast (more than about 7°) flow separation can be expected. In this case a severe drag increase is expected and the flow becomes unsteady. In the present design, the inner tube-cover serves to control the rate of flow deceleration and thus suppress flow separation. Moreover, the actual longitudinal location of the tube-cover along the diffuser may be set to optimize local flow conditions at the mosquito-delivery-ports. The use of an aerofoil element to reduce the air velocity sufficiently in the vicinity of mosquito-delivery-ports has not been attempted previously to the best of the inventors' knowledge.

[0131] The tube cover is now considered in greater detail. The tube cover may be provided as a fixed component, or may be removable to be attached for each flight or as needed.

[0132] The tube cover may have an aerofoil cross section, that is it may have a shape defined by a wing-like cross section, which shape provides less drag than for example having a pipe with a circular cross section.

[0133] As well as suppressing flow separation, the tube cover further may further serve to release the insects at the center of the diffuser, where the velocity is low. If, without the tube cover, one simply takes a pipe and releases the insects at the sides of the diffuser, the air velocity to which they are instantly exposed is high. A solution is to extend the pipe towards the center and then cover it with the tube cover to reduce drag.

[0134] Within the tube cover, inside and along the length of the diffuser, each one of the tubes ends at a specific port. The mosquitoes travel along different tubes and do not need to encounter junctions.

[0135] The main geometrical parameters controlling the low speed air and its extent have been defined as: [0136] 1) Diffuser length [0137] 2) Diffuser throat height [0138] 3) Diffuser exit height [0139] 4) Functional shape of the diffuser inner contours [0140] 5) Relative location of the tube cover and the diffuser

[0141] The following provides examples of different configurations, showing how tube cover and nozzle parameters, such as geometry, dimensions, and location within the diffuser can have effects on the performance of the diffuser and the effective distribution of the mosquitoes.

[0142] Reference is now made to FIG. 2 which illustrates the tube cover 200 taken alone. FIG. 3 shows the corresponding air flow.

[0143] As explained above the NACA-0018 standard shape is used. Due to the smooth external contour of this shape, flow separation is obtained only in the near wake of the blunt trailing edge section—16 in FIG. 1. The air flow analysis in FIG. 3 shows a small region of low velocity 300 at the exit of the tube. The area is too small to be useful for distributing mosquitoes.

[0144] Despite the success in obtaining a considerable reduction in the wake velocities trailing the tube cover alone, the tube cover solution by itself is not sufficient, due to the restricted region of low speed. The relevant low velocity region is of a few centimeters in length. As a result, the changes in the velocity are too large for the fragile insects.

[0145] Reference is now made to FIG. 4 which shows external diffusers 400 placed around the Tube Covers 402. FIG. 5 shows the corresponding air flow. The goal of using external diffusers 400 is reducing local air velocities approaching the tube cover 402. To achieve the goal, the two-dimensional (2D) tube cover has been located inside the subsonic diffuser.

[0146] A roll of these diffusers is to reduce the local air speed mainly above and beneath the tube cover and thus significantly increase the low speed region.

[0147] One possibility for the diffuser is to provide a linear diffuser, which is a subsonic diffuser based on the principle of a de-Laval converging-diverging nozzle. The added diffuser increases the longitudinal or chordwise extent of the low speed region downstream of the tube cover 402 to a length of about 10 cm. However, the height of the region barely changes relative to the case of the tube cover alone, thus again making the solution impractical as such.

[0148] The analysis shows that without having the tube cover 402 inside the diffuser, there are flow separations. As shown in FIG. 5, with the tube cover, the flow separations are prevented, thus allowing for a small size diffuser, which would otherwise not be possible.

[0149] Reference is now made to FIG. 6, which shows a cubic diffuser 600 around tube cover 602, and to the corresponding analysis in FIG. 7. Here the curvature of the diffuser is changed, resulting in an increase of the low velocity volume 700 at the exit point as shown in FIG. 7. Lower velocities overall were achieved in addition to the increase in the low velocity volume. As before, the presence of the Tube Cover 602 inside the diffuser helps set the rate of growth of the effective diffuser height, thus preventing massive flow separation. However there are high velocities at the throat.

[0150] Referring now to FIG. 8, the effect of a wide cubic diffuser is shown. Specifically, since the velocity at the throat for the cubic diffuser was very high, the inventors checked how the spacing between the upper and left parts of the diffuser affect the velocity at the throat. Specifically, upper and lower parts of the diffuser were moved apart, thereby doubling the throat height, marked by arrow 604 in FIG. 6. As a result, the maximum velocity at the throat, region 800 in FIG. 8, was reduced.

[0151] Reference is now made to FIG. 9 which an extended cubic diffuser 900, in which the diffuser exit area 902 is increased. The ambient velocity is thus decreased in the exit area 902, as shown in corresponding air velocity diagram FIG. 10. It is noted that the reduced velocity region in FIG. 10 extends well behind the end 904 of the nozzle in a plume shaped extension 906. The pipe cover is designated 904.

[0152] Reference is now made to FIG. 11 which is an air velocity diagram for a cubic diffuser with base bleed velocity.

[0153] In the preceding air velocity diagrams it is seen that sometimes the flow reduces, then increases, and then reduces again.

[0154] The flow is effected by parameters such as tube cover location, cover dimensions, diffuser dimensions and others, and we now consider analyzing the flow when blowing air outside of the tube covers by slightly pressurizing the pipe. The base of the tube cover is not assumed to be a solid wall, as before, but a longitudinal velocity of 1 m/s is specified exiting from the pipe. The velocity of 1 m/s was used in the analysis but a range of air velocities around the 1 m/s mark and above are also suitable. In fact, the higher the pipe velocity, the smaller the transition to the speed of the ambient air. The main upper constraint on the pipe air velocity is the effect on the insects.

[0155] The low speed region 1100 as shown in FIG. 11 extends over the width of the nozzle and has a plume shaped extension 1102. The 1 m/s base bleed velocity may achieve a significantly increase in the extent of the horizontal limits of the low speed flow region and considerable lengthening of the plume 1102 behind the nozzle. Furthermore, the base bleed velocity appears to eliminate the phenomenon of lower-higher-lower speed.

[0156] Additional options include having the blowing pipe, that is the pipe expelling the mosquitoes, set at some specific angle. Control of the quality of flow inside the diffuser can be manipulated by setting such angles, rather in the manner of a rotatable nozzle of a vectored thrust aircraft. Also each pipe may be set at a different angle.

[0157] In such an example, a low speed region behind the diffuser may extend to almost a meter long.

[0158] Reference is now made to FIG. 12, which is a simplified diagram showing air flow velocities resulting from the nozzle shape of FIG. 1 when air exits the insect delivery tube at a velocity of around 1 m/s. Again, an elongated region of reduced and gradually changing velocity 1200 emerges from behind the nozzle.

[0159] Reference is now made to FIG. 13, which is a simplified diagram showing air flow velocities resulting from a variation of the nozzle shape of FIG. 1 wherein the throat 1300 of the nozzle is widened. Again, air exits the insect delivery tube at a velocity of around 1 m/s, and an elongated region 1302 of gradually changing velocity emerges from behind the nozzle. As compared with FIG. 12, the elongated region is longer and smoother.

[0160] Reference is now made to FIG. 14 which illustrates the diffuser situated on the wing of an aircraft. As shown, the diffuser 1400 is mounted on struts 1402, 1404 to extend behind wing 1406, to serve as a sort of winglet. Multiple tubes within the winglet blow the mosquitoes along using a slight overpressure. Thus the tubes provide both the mosquitoes for distribution and the base velocity bleed for setting up the air volume.

[0161] The diffuser may use composite materials and may be a three-piece structure for easy transportation and lower cost, or a single piece construction for structural simplicity.

[0162] Reference numeral 1410 indicates a cross section of the diffuser and showing tube 1412 that provides the mosquitoes and base velocity bleed. Aerodynamically shaped tube cover 1414 is also shown. As with the nozzle, the tube cover may also be elongated to extend over the length of the diffuser.

[0163] As discussed above, for aircraft with a high-wing, an axisymmetric version of the diffuser may be provided.

[0164] It is expected that during the life of a patent maturing from this application many relevant insect control programs will be developed and the present embodiments may provide insect distribution for any such programs, and for any other purposes that may be developed, including pollination programs.

[0165] As used herein velocity values unless otherwise specified refer to the value given ±10%.

[0166] The terms “comprises”, “comprising”, “includes”, “including”, “having” and their conjugates mean “including but not limited to”.

[0167] The term “consisting of” means “including and limited to”.

[0168] As used herein, the singular form “a”, “an” and “the” include plural references unless the context clearly dictates otherwise.

[0169] It is appreciated that certain features of the invention, which are, for clarity, described in the context of separate embodiments, may also be provided in combination in a single embodiment, and the above description is to be construed as if this combination were explicitly written. Conversely, various features of the invention, which are, for brevity, described in the context of a single embodiment, may also be provided separately or in any suitable subcombination or as suitable in any other described embodiment of the invention, and the above description is to be construed as if these separate embodiments were explicitly written. Certain features described in the context of various embodiments are not to be considered essential features of those embodiments, unless the embodiment is inoperative without those elements.

[0170] Although the invention has been described in conjunction with specific embodiments thereof, it is evident that many alternatives, modifications and variations will be apparent to those skilled in the art. Accordingly, it is intended to embrace all such alternatives, modifications and variations that fall within the spirit and broad scope of the appended claims.

[0171] All publications, patents and patent applications mentioned in this specification are herein incorporated in their entirety by reference into the specification, to the same extent as if each individual publication, patent or patent application was specifically and individually indicated to be incorporated herein by reference. In addition, citation or identification of any reference in this application shall not be construed as an admission that such reference is available as prior art to the present invention. To the extent that section headings are used, they should not be construed as necessarily limiting.