Payload launching arrangement and a method for launching a payload

Patent metadata

Field	Value
Publication number	US-11919641-B2
Application number	US-201817257949-A
Country	US
Kind code	B2
Filing date	Aug 14, 2018
Priority date	Aug 14, 2018
Publication date	Mar 5, 2024
Grant date	Mar 5, 2024

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).

First claim

The invention claimed is:

1. A side-ways ejection arrangement ( 1 ) configured for storing and launching a payload ( 3 ), comprising:
a payload ( 3 ) stored and launched by the arrangement ( 1 ),
a push-out chamber ( 7 ),
a launch compartment ( 5 ) comprising an ejection device ( 4 ) configured to eject the payload ( 3 ) from the launch compartment ( 5 ) via the push-out chamber ( 7 ) to an airflow (AF) that, during use of the arrangement ( 1 ), flows over an aerodynamic surface ( 9 ) of the arrangement ( 1 ), and
an air intake ( 13 ) formed in the aerodynamic surface ( 9 ) and coupled to the 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 launch compartment ( 5 ) via the internal air transfer arrangement ( 17 ) such that the flow of air flowing into the launch compartment ( 5 ) will affect the payload ( 3 ) being ejected with an additional push-out force, and
an eject force of the ejection device ( 4 ) is added with said additional push-out force.

2. The arrangement ( 1 ) according to claim 1 , wherein at least one of the air intake ( 13 ) or the openable closure member ( 11 ) 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 launch compartment ( 5 ) via the internal air transfer arrangement ( 17 ).

3. The arrangement ( 1 ) according to claim 1 , wherein at least one of the air intake ( 13 ) or the openable closure member ( 11 ) is 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 launch compartment ( 5 ) via an internal duct arrangement provided between the air intake ( 13 ) and the launch compartment ( 5 ).

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) at least one of: in a direction opposite or nearly opposite the direction of the airflow (AF), 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 (α) relative the normal (N) to the centre line (CL) of the arrangement ( 1 ).

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

10. A method for launching a payload ( 3 ) by means of a side-ways ejection-arrangement ( 1 ) that comprises an ejection device ( 4 ) 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 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 launch compartment ( 5 ) from the air intake ( 13 ), the air intake ( 13 ) is configured to transfer flow of air to the 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, and wherein an elect force of the ejection device ( 4 ) is added with said 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 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).

Assignees

• Saab Ab

Inventors

• Bystroem Gunnar

Classifications

• B64D1/02 Primary

  Dropping, ejecting, or releasing articles (jettisonable fuel reservoirs B64D37/12) · CPC title

• F41H11/02 Primary

  Anti-aircraft or anti-guided missile {or anti-torpedo} defence installations or systems (cartridges or missiles for producing smoke or for dispensing radar chaff or infrared material F42B5/15, F42B12/48, F42B12/70; {informative reference: details of radar or sonar systems G01S7/00; jamming or electronic countermeasures G01S7/38, G01S7/495, H04K3/00}) · CPC title

• F41F7/00

  Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, {e.g. using spigots}(F41F3/04 takes precedence; {centrifugal sling apparatus F41B3/04}) · CPC title