Aircraft capture systems

• US 5,054,717 A
• Filed: 04/16/1990
• Issued: 10/08/1991
• Est. Priority Date: 05/03/1989
• Status: Expired due to Fees

• Current Assignee: GEC Marconi Limited (Gooding Consumer Electronics Ltd.)
• Original Assignee: GEC Marconi Limited (Gooding Consumer Electronics Ltd.)
• Inventors: Taylor, Douglas R.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): BIDWELL, ANNE
• Application Number:
  US07/509,604
• Time in Patent Office: 540 Days
• Field of Search: 244/110 F, 244/110 R, 244/114 R, 244/115, 244/116, 258/1.2, 258/1.8, 258/11-26, 114/258, 114/261, 114/262
• US Class Current: 244/110.00F
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64F 1/029 using a cable or tether
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 70/30 for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net

Abstract

An aircraft capture system, e.g. for a radio-controlled pilotless aircraft (19), having at the homing station a boom arrangement (13) mounted for rotation about a vertical hinge axis (A--A) and having appreciable flexibility under forces acting perpendicular to the hinge axis while being substantially inflexible under forces acting parallel to the hinge axis. The flexibility of the boom arrangement cushions the aircraft against shock when an arrester hook (33) deployed from the aircraft engages the boom arrangement via an arrester wire (15) attached to the boom arrangement.

Claims

1. An aircraft capture system comprising:

a homing station at which an aircraft is captured;

an elongate boom arrangement at the homing station mounted for pivotal movement about a substantially vertical hinge axis;

a first elongate flexible arrester member connected at one end to said boom arrangement at a position spaced from said hinge axis;

energy absorber means at the homing station connected to the other end of said first arrester member;

a second elongate flexible arrester member connected at one end to the aircraft;

arrester hook means attached to said second arrester member at a position spaced from said one end of said second arrester member; and

aerodynamic lift means operable when deployed, with the aircraft in flight, to support said second arrester means by aerodynamic lift action;

said boom arrangement being appreciably flexible under forces applied thereto in a direction substantially perpendicular to the hinge axis whilst being substantially inflexible under forces applied thereto in a direction parallel to the hinge axis.

2. A system according to claim 1 wherein said boom arrangement is appreciably flexible under forces applied thereto in a direction substantially perpendicular to said hinge axis in the direction of the length of the boom arrangement.

3. A system according to claim 2 wherein said boom arrangement is substantially inflexible under forces applied thereto in a direction substantially perpendicular to said hinge axis at right angles to the length of the boom arrangement.

4. A system according to claim 3 wherein the boom arrangement comprises first and second confronting oppositely curved boom members convergent towards their ends to define end junctions, the inboard end junction being located at said vertical hinge axis and each said boom member being thicker in a direction parallel to the hinge axis than in an orthogonal direction.

5. A system according to claim 4 wherein at the outboard end junction of the convergent boom members there is a swivel attachment having a swivel axis parallel to the length of the boom arrangement and the first arrester member is connected at said one end to said swivel attachment.

6. A system according to claim 1 wherein said first and second arrester members comprise wires.

7. A system according to claim 1 wherein said energy absorber means is a hydraulic damper mechanism.