Payload launching arrangement and a method for launching a payload

1. An arrangement ( 1 ) configured for storing and launching a payload ( 3 ) to be launched from the arrangement ( 1 ), the arrangement ( 1 ) comprising:

an elongated body ( 9 ) comprising:

a compartment ( 15 ) configured to store and eject the payload ( 3 ), and

an aerodynamic surface ( 11 ) provided with a launch opening ( 13 ) comprising a guideway ( 17 ) extending from the compartment ( 15 ) obliquely downwards and backwards relative to a flight travel direction (D) of the payload ( 3 ), the guideway ( 17 ) being coupled to or associated with a payload holding area ( 22 ) of an end section ( 24 ) of the compartment ( 15 ), the payload holding area ( 22 ) being configured to hold the payload ( 3 ) to be launched in an eject position (EJ) stored in the compartment ( 15 ),

wherein:

a sliding portion ( 12 ) of the payload ( 3 ) is configured to slide along the guideway ( 17 ) and through the launch opening ( 13 ) upon ejection,

an extension of the guideway ( 17 ) inclines with an acute angle (a) relative the normal (N) to the centre line (CL) of the elongated body ( 9 ), the acute angle (a) being inclined backwards relative to the flight travel direction (D),

the plane of the payload area ( 22 ) and the plane of the guideway ( 17 ) exhibit a relative angle corresponding to the acute angle (α), which relative angle forms a corner point (CP),

the payload holding area ( 22 ) has an ejection mechanism ( 21 ) configured to eject the payload ( 3 ) along the payload holding area ( 22 ) in a direction toward the launch opening ( 13 ) for providing a motion of the payload ( 3 ) over the corner point (CP), such that a first portion ( 23 ) of the payload ( 3 ) is exposed to an airflow (AF) created by travel in the flight travel direction (D) before a second portion ( 28 ) of the payload ( 3 ) is exposed to the airflow,

the sliding portion ( 12 ) is opposite an opposite side of the payload ( 3 ) comprising the first portion ( 23 ) and the second portion ( 28 ),

the acute angle (α) is such that, during use of the arrangement, airflow flowing over the aerodynamic surface applies an eject force on the first portion of the payload being ejected and the second portion ( 28 ) of the payload ( 3 ) is exposed to the airflow after the first portion has been exposed thereto, such that the payload will flip around for releasing a countermeasure element ( 25 ) from the payload ( 3 ) by means of the airflow;

the aerodynamic surface ( 11 ) lies wholly in a first plane; and

the extension of the guideway ( 17 ) intersects and continues obliquely downwards and backwards beyond the first plane with an incline oriented at the acute angle (α).

2. The arrangement ( 1 ) according to claim 1 , wherein a gradient of the direction of the airflow (AF) flowing over the aerodynamic surface ( 11 ), during use of the arrangement ( 1 ), with respect to the incline of the extension of the guideway ( 17 ) exhibits an obtuse angle (( 3 ) defined externally the launch opening ( 13 ) in a direction toward a fore end (FE) of the arrangement ( 1 ) and seen in a direction outward from the aerodynamic surface ( 11 ).

3. The arrangement ( 1 ) according to claim 1 , wherein the extension of the guideway ( 17 ) extends a distance outward from and beyond a major part of the aerodynamic surface ( 11 ).

4. The arrangement ( 1 ) according to claim 1 , wherein the acute angle (α) is between 10° to 60°.

5. An aerial vehicle ( 5 ) configured to carry the arrangement ( 1 ) according to claim 1 .

6. A method for launching a payload ( 3 ) from an arrangement ( 1 ), the method comprising the steps of:

providing the arrangement ( 1 ) comprising an elongated body ( 9 ) comprising:

a compartment ( 15 ) configured to store and eject the payload ( 3 ) that is to be launched from the arrangement ( 1 ), and

an aerodynamic surface ( 11 ) provided with a launch opening ( 13 ) comprising a guideway ( 17 ) extending from the compartment ( 15 ) obliquely downwards and backwards relative to a flight travel direction (D) of the payload ( 3 ), the guideway ( 17 ) being coupled to or associated with a payload holding area ( 22 ) of an end section ( 24 ) of the compartment ( 15 ), the payload holding area ( 22 ) being configured to hold the payload ( 3 ) to be launched in an eject position (EJ) stored in the compartment ( 15 ),

wherein:

a sliding portion ( 12 ) of the payload ( 3 ) is configured to slide along the guideway ( 17 ) and through the launch opening ( 13 ) upon ejection,

an extension of the guideway ( 17 ) inclines with an acute angle (α) relative the normal (N) to the centre line (CL) of the elongated body ( 9 ), the acute angle (α) being inclined backwards relative to the flight travel direction (D),

a plane of the payload area ( 22 ) and a plane of the guideway ( 17 ) exhibit a relative angle corresponding to the acute angle (α), which relative angle forms a corner point (CP),

the payload holding area ( 22 ) has an ejection mechanism ( 21 ) configured to eject the payload ( 3 ) along the payload holding area ( 22 ) in a direction toward the launch opening ( 13 ) for providing a motion of the payload ( 3 ) over the corner point (CP), such that a first portion ( 23 ) of the payload ( 3 ) is exposed to an airflow (AF) created by travel in the flight travel direction (D) before a second portion ( 28 ) of the payload ( 3 ) is exposed to the airflow,

the sliding portion ( 12 ) is opposite an opposite side of the payload ( 3 ) comprising the first portion ( 23 ) and the second portion ( 28 ),

the acute angle (α) is such that, during use of the arrangement, an airflow (AF) flowing over the aerodynamic surface applies an eject force on the first portion of the payload being ejected,

the aerodynamic surface ( 11 ) lies wholly in a first plane, and

the extension of the guideway ( 17 ) intersects and continues obliquely downwards and backwards beyond the first plane with an incline oriented at the acute angle (α),

positioning the payload ( 3 ) to be launched in the eject position (EJ);

ejecting the payload ( 3 ) along the extension of the guideway ( 17 ) and at the acute angle (α) inclined backwards relative to the flight travel direction (D) and with the airflow (AF) flowing over the aerodynamic surface;

exposing the payload ( 3 ) to the airflow (AF) flowing over the aerodynamic surface ( 11 ), such that the eject force applied, via the airflow (AF) in the same direction as ejection, on the first portion of the payload being ejected will cause the payload to flip around before the second portion of the payload ( 3 ) is exposed to the airflow; and

upon flipping around of the payload, releasing a countermeasure means ( 25 ) from the payload by means of the airflow (AF).

7. The method according to claim 6 , the method comprises the step of:

ejecting the payload ( 3 ) along the extension of the guideway ( 17 ), wherein the acute angle (α) is between 10° to 60°.

8. The method according to claim 7 , wherein the acute angle is between 20° to 45°.

9. The arrangement ( 1 ) according to claim 1 , wherein the acute angle is between 20° to 45°.