PAYLOAD LAUNCHING ARRANGEMENT AND A METHOD FOR LAUNCHING A PAYLOAD

Abstract

The present invention concerns a method for launching a payload (3) by means of an arrangement (1), which is configured for storing and launching a payload (3). A launch compartment (5) of the arrangement (1) is configured to eject the payload (3) from the launch compartment (5) via a push-out chamber (7) to an airflow (AF), which during use of the arrangement (1) flows over an aerodynamic surface (9) of the arrangement (1). An air intake (13) is formed in the aerodynamic surface (9) and is coupled to the push-out chamber (7) and/or launch compartment (5) via an internal air transfer arrangement (17) comprising an openable closure member (11) configured to close and open the internal air transfer arrangement (17).

Claims

1. A side-ways ejection arrangement (1) configured for storing and launching a payload (3), a launch compartment (5) of the arrangement (1) is configured to eject the payload (3) from the launch compartment (5) via a push-out chamber (7) to an airflow (AF), which during use of the arrangement (1) flows over an aerodynamic surface (9) of the arrangement (1), an air intake (13) is formed in the aerodynamic surface (9) and is coupled to the push-out chamber (7) and/or launch compartment (5) via an internal air transfer arrangement (17) comprising an openable closure member (11) configured to close and open the internal air transfer arrangement (17), wherein the air intake (13) is configured to transfer flow of air to the push-out chamber (7) and/or launch compartment (5) via an internal air transfer arrangement (17); the flow of air flowing into the launch compartment (5) will affect the payload (3) being ejected with an additional push-out force.

2. The arrangement (1) according to claim 1, wherein the air intake (13) and/or the openable closure member (11) being configured to, in an open state and during use of the arrangement (1), lead a separated flow of air (SAF) divided from the airflow (AF) into the push-out chamber (7) and/or the launch compartment (5) via the internal air transfer arrangement (17).

3. The arrangement (1) according to claim 1, wherein the air intake (13) and/or the openable closure member (11) being configured to form a low-drag air inlet.

4. The arrangement (1) according to claim 1, wherein the air intake (13) is configured to allow a separated flow of air (SAF) into the push-out chamber (7) via an internal duct arrangement provided between the air intake (13) and the push-out chamber (7).

5. The arrangement (1) according to claim 1, wherein the internal air transfer arrangement (17) is configured to direct a separated flow of air (SAF) in a direction opposite or nearly opposite the direction of the airflow (AF) and/or in a direction inclining obliquely downwards and forwards relative to the flight direction (FD).

6. The arrangement (1) according to claim 1, wherein a sliding portion of the payload (3) is configured, during launching, to be able to slide along a guideway (19) extending within the push-out chamber (7) from the launch compartment (5) to a launch opening (21).

7. The arrangement (1) according to claim 6, wherein the extension of the guideway (19) extends a distance outward from and beyond the aerodynamic surface (9)e by means of a protruding ramp (20).

8. The arrangement (1) according to claim 6, wherein the extension of the guideway (19) inclines with an acute angle (a) relative the normal (N) to the centre line (CL) of the arrangement (1).

9. An aerial vehicle (15) configured to carry the arrangement (1) to claim 1.

10. A method for launching a payload (3) by means of a side-ways ejection-arrangement (1) configured to eject the payload (3) from a launch compartment (5) via a push-out chamber (7) to an airflow (AF), which during use of the arrangement (1) flows over an aerodynamic surface (9) of the arrangement (1), wherein an air intake (13) is formed in the aerodynamic surface (9) and is coupled to the push-out chamber (7) and/or launch compartment (5) via an internal air transfer arrangement (17) comprising an openable closure member (11) configured to close and open the internal air transfer arrangement (17), the method comprises the steps of: loading the launch compartment (5) with the payload (3) to be launched; opening the openable closure member (11) for dividing a separated flow of air (SAF) from the airflow (AF) and leading the separated flow of air (SAF) into the push-out chamber (7) and/or launch compartment (5) from the air intake (13), the air intake (13) is configured to transfer flow of air to the push-out chamber (7) and/or launch compartment (5) via an internal air transfer arrangement (17), wherein the flow of air flowing into the launch compartment (5) will affect the payload (3) being ejected with an additional push-out force; ejecting the payload (3) from the launch compartment (5); and closing the openable hatch member (11).

11. The method according to claim 10, wherein the method comprises the further step of: leading the separated flow of air (SAF) into the push-out chamber (7) and/or launch compartment (5) in such way that the separated flow of air (SAF) is directed in a direction opposite or nearly opposite the direction of the airflow (AF) and/or is directed in a direction that inclines obliquely downwards and forwards relative to the flight direction (FD).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0076] The present disclosure herein will now be described by way of examples with references to the accompanying schematic drawings, of which:

[0077] FIG. 1 illustrates an arrangement configured for storing and launching a payload according to a first example;

[0078] FIG. 2 illustrates an arrangement configured for storing and launching a payload according to a second example;

[0079] FIG. 3 illustrates an arrangement configured for storing and launching a payload according to a third example;

[0080] FIG. 4 illustrates an arrangement configured for storing and launching a payload according to a fourth example;

[0081] FIG. 5 illustrates a flowchart showing an exemplary method for launching a payload; and

[0082] FIG. 6 illustrates a flowchart showing an exemplary method for launching a payload.

DETAILED DESCRIPTION

[0083] Hereinafter, examples of the present invention will be described in detail with reference to the accompanying drawings, wherein for the sake of clarity and understanding of the invention some details of no importance may be deleted from the drawings. Some details may have the same reference number but belong to different examples and shows a generic feature.

[0084] FIG. 1 illustrates an arrangement 1 configured for storing and launching a payload 3 according to a first example. The arrangement 1 comprises a launch compartment 5 configured to eject the payload 3 from the launch compartment 5 via a push-out chamber 7 to an airflow AF, which during use of the arrangement 1 flows over an aerodynamic surface 9 of the arrangement 1. The aerodynamic surface 9 is provided with an openable hatch member 11 configured to cover an air intake 13 connected to the push-out chamber 7.

[0085] The arrangement 1 may be carried by an aerial vehicle 15 and is adapted for sideways ejection of the payload 3.

[0086] The air intake 13 may be designed to allow separated flow (not shown) of air into the push-out chamber 7 via an internal duct arrangement (not shown) arranged within the arrangement 1 between the air intake 13 and the push-out chamber 7.

[0087] In such way is achieved that, when the arrangement 1 is moved through the air in a flight direction FD and the air flows over the aerodynamic surface 9 as an airflow AF, separated flow of air flowing into the push-out chamber 7 will affect the payload 3 being ejected with an additional push-out force.

[0088] By means of wind tunnel experiments made by the applicant it has been shown that the additional push-out force also may flip around the payload 3. Such rotation of the payload 3 is beneficial for releasing a countermeasure element (not shown) from the payload 3 by means of the airflow AF.

[0089] FIG. 2 illustrates an arrangement 1 configured for storing and launching a payload 3 according to a second example. The arrangement 1 comprises a launch compartment 5 configured to eject the payload 3 from the launch compartment 5 via a push-out chamber 7 to an airflow AF, which during use of the arrangement 1 flows over an aerodynamic surface 9 of the arrangement 1.

[0090] The launch compartment 5 is provided with an ejection mechanism 6 configured to push-out the payload 3. The aerodynamic surface 9 is provided with an openable hatch member 11 configured to cover an air intake 13 connected to the push-out chamber 7. The air intake 13 and the openable hatch member 11 being configured in an open state to, during use of the arrangement 1, lead a separated flow of air SAF divided from the airflow AF into the push-out chamber 7 from the air intake 13 to the payload 3 via an internal duct arrangement 17. The separated flow of air SAF flowing into the push-out chamber 7 will affect the payload 3, being ejected by means of the ejection mechanism 6, with an additional push-out force F.

[0091] The air intake 13 may be designed to allow the separated flow of air SAF into the push-out chamber 7 via the internal duct arrangement 17 provided between the air intake 13 and the push-out chamber 7.

[0092] The internal duct arrangement 17 may be configured to redirect the separated flow of air SAF in a direction opposite or any suitable direction for affecting the payload 3 with the additional push-out force F.

[0093] The ejection mechanism 6 is configured to eject the payload 3 along a guideway 19 extending from the launch compartment to a launch opening 21 via the push-out chamber 7, which guideway 19 may entirely be inclined relative the flight direction or partly inclined.

[0094] The launch opening 21 is provided in the aerodynamic surface 9 and is coupled or associated with the launch compartment 5 via the push-out chamber 7 for providing an open connection between the launch compartment 5 and the airflow AF.

[0095] The arrangement 1 may comprise an air intake 13 formed as a submerged 14 air inlet (broken line as an example) comprising curved walls recessed into the aerodynamic surface so that the air intake 13 and/or the openable hatch member 11 will operate as a low-drag air inlet.

[0096] A sliding portion of the payload may be configured, during launching, to be able to slide along the guideway 19 extending within the push-out chamber 7 from the launch compartment 5 to the launch opening 21.

[0097] The extension of the guideway 19 may extend a distance outward from and beyond the aerodynamic surface by means of a protruding ramp 20.

[0098] The extension of the guideway 19 may incline with an acute angle α relative the normal N to the centre line CL of the arrangement 1.

[0099] The acute angle α may be between 10° to 60°, preferably between 20° and 45°.

[0100] The acute angle α may be determined in such a way that, during use of the arrangement 1, airflow AF flowing over the aerodynamic surface 9 will apply an additional impetus Ai on a first portion of the payload 3 being ejected, so that the payload 3 will flip around for releasing a countermeasure element (not shown) by means of the airflow, which countermeasure element is arranged to the payload 3.

[0101] FIG. 3 illustrates an arrangement 1 configured for storing and launching a payload 3 according to a third example. The arrangement 1 comprises a launch compartment 5 configured with an eject mechanism 6 configured to eject the payload 3 from the launch compartment 5 via a push-out chamber 7 to an airflow AF, which during use of the arrangement 1 flows over an aerodynamic surface 9 of the arrangement 1. The aerodynamic surface 9 is provided with an openable hatch member 11 configured to cover an air intake 13 coupled to the push-out chamber 7 and/or launch compartment 5 via an internal air transfer arrangement 17.

[0102] The openable hatch member 11 may be operated by a drive unit 22, which in turn is coupled to a control unit (not shown) configured to operate the openable hatch member 11 in a variable manner for affecting the payload 3 with a proper additional push-out force F depending upon the attitude and the velocity of the aerial vehicle (not shown) carrying the arrangement 1.

[0103] In such way is achieved that, when the arrangement 1 is moved through the air in a flight direction FD, and the air flows over the aerodynamic surface 9 as an airflow AF, the flow of air flowing into the push-out chamber 7 and/or launch compartment 5, will affect the payload 3 (being ejected) with an additional push-out force F. In such way the eject force produced by the eject mechanism 6 can be added with an additional push-out force F. In such way is provided that a rapid sideway ejection of the payload 3 can be achieved.

[0104] The arrangement is moved through the air along a flight direction, wherein the air flows over the aerodynamic surface as an airflow AF. The payload 3 being ejected will be affected by an additional force generated by the airflow AF providing that a rapid sideway ejection of the payload 3 is achieved. A direction pointing from the fore end to the aft end fully or essentially corresponds with the direction of an airflow AF flowing over the aerodynamic surface.

[0105] An imaginary inclining line of the guideway defines the inclination of the guideway, wherein the inclining line inclines toward the aft end AE and thus inclines “with” the airflow AF. The airflow AF will apply an additional force on the payload being ejected, which additional force assists and supports the ejection of the payload further sideways. In such way the ejected payload will be affected by an additional force F generated by the airflow AF providing that a rapid sideway ejection of the payload is achieved.

[0106] FIG. 4 illustrates an arrangement 1 configured for storing and launching a payload 3. The arrangement comprises a launch compartment 5 configured to eject the payload 3 from the launch compartment 5 by means of an electro-pyrotechnical ejection device 4. The payload 3 is ejected to an airflow AF, which during use of the arrangement flows over an aerodynamic surface 9 of the arrangement 1. The payload 3 is ejected via a push-out chamber 7, which is integrally arranged with the launch compartment 5. An air intake 13 is formed in the aerodynamic surface 9 and is coupled to the launch compartment 5 via an internal air duct 17 comprising an openable closure member 11 configured to close the internal air duct 17. The air intake 13 and the openable closure member 11 may be configured to, in an open state and during use of the arrangement, lead a separated flow of air SAF divided from the airflow AF into the launch compartment 5 via the internal air duct 17. In such way is achieved that the payload 3 will be affected by an additional push-out force which is applied in a direction outward from the arrangement 1.

[0107] FIG. 5 illustrates a flowchart showing an exemplary method for launching a payload of an arrangement 1 configured to eject the payload from the launch compartment via a push-out chamber to an airflow, which during use of the arrangement flows over an aerodynamic surface of the arrangement, wherein an air intake is formed in the aerodynamic surface and is coupled to the push-out chamber and/or launch compartment via an internal air transfer arrangement comprising an openable closure member configured to close the internal air transfer arrangement. The method starts with step 501. In a second step 502 the method is performed. In a third step 503 the method is stopped. The step 502 may comprise the steps of; loading the launch compartment with the payload; opening the openable closure member for dividing a separated flow of air from the airflow and leading the separated flow of air into the push-out chamber and/or launch compartment from the air intake; ejecting at least one payload from the launch compartment; and closing the openable hatch member.

[0108] FIG. 6 illustrates a further example of a method for launching the payload from an arrangement 1 as defined in FIG. 5. The exemplary method starts with step 601. A second step 602 comprises loading the launch compartment with the payload. A third step 603 comprises the step opening the openable closure member for dividing a separated flow of air from the airflow. A fourth step 604 comprises leading the separated flow of air into the push-out chamber and/or launch compartment from the air intake and leading the separated flow of air into the push-out chamber and/or launch compartment in such way that the separated flow of air (SAF) is directed in a direction opposite or nearly opposite the direction of the airflow (AF) and/or is directed in a direction that inclines obliquely downwards and forwards relative to the flight direction. A fifth step 605 comprises ejecting at least one payload from the launch compartment. A sixth step 606 comprises closing the openable closure member. In a seventh step 607 the method is stopped.

[0109] The present invention is of course not in any way restricted to the examples described above, but many possibilities to modifications, or combinations of the examples, thereof should be apparent to a person with ordinary skill in the art without departing from the basic idea of the invention as defined in the appended claims.