Reconnaissance system comprising an air-borne vehicle rotating about its longitudinal axis

• US 4,543,603 A
• Filed: 11/10/1983
• Issued: 09/24/1985
• Est. Priority Date: 11/30/1982
• Status: Expired due to Term

• Current Assignee: Aerospatiale Societe Nationale Industrielle
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Laures, Pierre
• Primary Examiner(s): Britton, Howard W.
• Assistant Examiner(s): Kostak, Victor R.
• Application Number:
  US06/550,538
• Time in Patent Office: 684 Days
• Field of Search: 358/109, 358/113, 358/108, 358/99, 356/4, 250/330, 250/331, 250/332, 250/334, 364/456, 244/3.16
• US Class Current: 348/145
• CPC Class Codes: F41G 7/222 for spin-stabilized missiles
• CPC Class Codes: F41G 7/343 comparing observed and stored data of target position or of distinctive marks along the path towards the target
• CPC Class Codes: G01C 11/025 by scanning the object

Abstract

The invention relates to a reconnaissance system comprising an air-borne vehicle capable of moving above a territory to be surveyed by rotating about its longitudinal axis, and means for taking images disposed on board the vehicle to observe said territory by a helicoidal scanning in relation with the rotation of the vehicle, wherein the vehicle is of the self-propelled missile type and the sensitive members are formed by at least one linear assembly of photosensitive elements disposed parallel to the longitudinal axis of the missile to give at each line an image of an elementary strip of territory, which scans a strip of territory upon each revolution of the missile, the total image of the territory being formed by the plurality of images of the successive strips.

Claims

1. A reconnaissance system capable of making a reconnaissance of long duration and of long flying range over an enemy territory comprising:

a self-propelled missile capable of making manoeuvres of short duration and high acceleration and moving above said territory along a path by rotating about its longitudinal axis;

a photosensitive detector assembly fixedly attached to said self-propelled missile in a fixed rotating relationship with said missile, for giving an image of said territory;

said photosensitive detector assembly comprising at least one linear arrangement of photosensitive elements arranged parallel to said longitudinal axis of said missile, so that, at an instant during which it is directed towards said territory, said linear arrangement observes an elementary strip of said territory whose length is parallel to the corresponding instantaneous part of said path, such successive elementary strips scanning a wide strip of said territory transverse to said part of path as said missile rotates about its longitudinal axis and said image being formed by such successive transverse wide strips, as said missile moves along its path.

2. The reconnaissance system of claim 1, wherein said photosensitive detector assembly comprises three detectors, each having at least one linear arrangement of photosensitive elements, arranged parallel to the longitudinal axis of said missile, said detectors being equally distributed about said longitudinal axis of said missile, the opening of each detector being 120°

.

3. The reconnaissance system of claim 1, comprising a unit for restitution on photographic film of the images picked up by said photosensitive detector assembly, wherein said restitution unit comprises a laser source whose beam is modulated by the electrical signals coming from said photosensitive elements and deviated by a saw-tooth signal whose period is equal to the duration of read-out of the photosensitive elements giving lines of scanning of a partial PG,17 image, then focussed on a film driven longitudinally at a speed proportional to that of the missile.

4. The reconnaissance system of claim 1, comprising a unit for restitution on photographic film of the images picked up by said photosensitive detector assembly, wherein said restitution unit comprises a laser source whose beam is modulated by the electrical signals coming from said photosensitive elements and deviated by a rotating mirror creating the displacement of the beam in register with the read-out of the photosensitive elements of the scanning lines, then focused on a film driven longitudinally at a speed proportional of that of said missile, and transversely to a speed proportional to the angle of roll.