WO2000004336A1

WO2000004336A1 - Protective cover for a window

Info

Publication number: WO2000004336A1
Application number: PCT/GB1999/002281
Authority: WO
Inventors: John Wilfrid Phillips
Original assignee: Matra Bae Dynamics UK Ltd
Current assignee: Matra Bae Dynamics UK Ltd
Priority date: 1998-07-17
Filing date: 1999-07-15
Publication date: 2000-01-27
Anticipated expiration: 2001-01-17
Also published as: AU4922799A; JP2000513802A; GB9815473D0

Abstract

This invention relates to the field of protective covers for optical and/or electromagnetic windows utilised by sensor systems. The invention provides apparatus enabling the protection of such windows, and the removing of the protected covers by the application of a specified level of heat energy.

Description

PROTECTIVE COVER FOR A WINDOW

This invention relates to the field of protective covers, and more particularly, but not exclusively to such covers for use in the protection of optical and/or electromagnetic windows used by missile sensor systems.

In the field of guided weapon sensor technology, one particular problem identified as being capable of reducing the probability of successful target acquisition, tracking and detonation is that of contamination and/or obscuration of sensor windows by debris. Such debris can originate from a number of

sources, be they environmental or a consequence of the missile storage and operation. The reduction and/or limitation of the obscuration of sensor viewing windows would undoubtedly improve the reliability and effectiveness of guided

weapon systems, and in turn reduce the overall costs for users associated with unsuccessful launches and use.

Our invention seeks to provide a simple and cost effective method and

apparatus to enable the protection of sensor viewing windows by utilising materials which exhibit temperature dependant adhesive characteristics.

Accordingly there is provided a releasable protective cover means for a sensor window, comprising at least one element of a protective material, said element being releasably attached to a surface of a vehicle body, said element being so designed as to become separated from said body on the application

of a specified level of heat energy. ln an embodiment of the invention, the apparatus comprises a self

adhesive material.

In a further embodiment of the invention, the apparatus comprises a strip of material formed around the outer diameter of a body, each end of the material being realisably fastened by an adhesive.

An example of an embodiment of the invention will now be described by way of example only with reference to the following drawings in which :

Figure 1 shows a diagrammatic representation of a guided missile showing the typical positioning of a pair of seeker system windows

Figure 2 shows a diagrammatic view of the nose section of a guided missile as shown in figure 1 employing one embodiment of the invention, and;

Figure 3 shows a diagrammatic view of the nose section of a guided missile as shown in figure 1 employing a second further embodiment of the

invention.

In Figure 1 , a typical guided missile outer profile is shown 2, having a

nose section 4 typically containing missile sensors, a main body section 6, and a tail section 8 comprising the missile control surfaces. Sensor system windows 10 are shown housed in the nose section 4 lying in this particular example at two circumferential locations at the same longitudinal position on

the missile body 2.

In Figure 2, the missile nose section 2 is shown, with discrete protective material patch elements 12 in accordance with the invention placed over each of the sensor windows shown 10. The protective materials 12 could themselves posses self adhesive properties, or a suitable adhesive could be applied to the surface of the missile body surrounding the window location 10 and the material subsequently affixed thereto.

Figure 3 shows the missile nose cone section 2 and seeker window

locations 10, but in this particular embodiment a strip of material 14 is located around the circumference of the missile nose cone 4 such that it covers both seeker window locations 10. Figure 4 shows a strip or band of such material 14 having an adhesive applied of integral with an end position 16 such that when the strip or band is placed around the body of the nose cone 4 covering the windows 10 the strip or band will be fixedly held in position. Alternatively

instead of the strip or band being in one section surrounding the missile body 2, it can be segmented 20 and could be held in position either by a number of integral adhesive positions 16, 18, or the whole strip or band held by an

adhesive tape.

In use, either of the example embodiments described in the figures

could be attached to the missile as described either at the stage of

manufacture or as a retrofit where particular in service conditions prevail which increase the likelihood of sensor window contamination. Examples of such environments include those with high humidity, high salt content (i.e. in sea- bourne applications) and areas of high dust and/or sand particle levels, along

with launch debris and missile efflux. The mechanism of release for either the patch elements 2 or the strip or band elements 10 would be via the application of heat energy due to the kinematic heating associated with the missiles flight. The adhesives used to

locate either the patches 12 or the strips or bands 14 to the missile body 2

would be designed such that their adhesive properties would degrade in flight to a level where aerodynamic forces would result in the separation of said patches 12 and/or strips or bands 14, thereby leaving the sensor windows with a substantially uncontaminated surface through which to view.

The adhesives used to maintain the patches and/or strips or bands in situ during launch of the missile could comprise tape or other such carrying medium along with directly applied brush or spray on adhesives.

The term sensor window comprises such windows associated with missile fusing sensors and with sensors relating to seekers, guidance systems, early warning and electronic warfare equipment, along with such sensor

windows found on aircraft.

Claims

A releasable protective cover means for a sensor window, comprising at least one element of a protective material, said element being releasably attached to a surface of a vehicle body, said element being so designed as to separate from said body on the application of a specified level of heat energy A protective cover means according to claim 1 wherein said material has self adhesive properties A protective cover means according to claims 1 or 2 wherein said material is substantially metallic A protective cover means according to claim 1 wherein said element comprises a strip or band of material fastened by an adhesively bonded joint A protective cover means according to claim 4 wherein said strip or band of material is segmented, the individual segments being so located on the missile as to substantially form a continuous strip or band around the missile body A protective cover means according to claims 1 , 2 or 3 wherein said material is a discrete patch element A protective cover means according to any of the preceding claims 1 to 6 wherein said vehicle is a missile A protective cover means according to any of the preceding claims 1 to 6 wherein said vehicle is an aircraft A protective cover means substantially as hereinbefore described in accordance with the accompanying drawings