U.S. patent number 3,901,444 [Application Number 05/509,199] was granted by the patent office on 1975-08-26 for window wash system.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Air. Invention is credited to Glenn W. Albright, Dale E. Maltbie.
United States Patent |
3,901,444 |
Maltbie , et al. |
August 26, 1975 |
Window wash system
Abstract
A window wash system for the inflight cleaning of aircraft
windows having a washing fluid storage tank and nozzles adjacent
the windows to be cleaned. In addition to the washing fluid within
the storage tank, gas under pressure is also contained therein.
Through a series of valves, either washing fluid may be dispensed
through the nozzles or gas may be dispensed through the entire
system for purging the system. The window wash system of this
invention is capable of reliable operation under adverse conditions
such as high speed flight or variable temperature and
pressures.
Inventors: |
Maltbie; Dale E. (Wichita,
KS), Albright; Glenn W. (Wichita, KS) |
Assignee: |
The United States of America as
represented by the Secretary of the Air (Washington,
DC)
|
Family
ID: |
24025697 |
Appl.
No.: |
05/509,199 |
Filed: |
September 25, 1974 |
Current U.S.
Class: |
239/112; 222/148;
239/284.1; 239/305 |
Current CPC
Class: |
B60S
1/54 (20130101); B60S 1/481 (20130101) |
Current International
Class: |
B60S
1/48 (20060101); B60S 1/02 (20060101); B60S
1/46 (20060101); B60S 1/54 (20060101); B05b
001/10 (); B05b 015/02 () |
Field of
Search: |
;239/130,305,112,284,304,303,302,171 ;222/148 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Wood, Jr.; M. Henson
Assistant Examiner: Mar; Michael
Attorney, Agent or Firm: Rusz; Joseph E. Erlich; Jacob
N.
Claims
We claim:
1. A window wash system for inflight cleaning of aircraft windows
comprising means for storing a washing fluid and a gas therein,
means for dispensing said washing fluid, first means connecting
said storage means to said dispensing means, second means
connecting said storage means to said dispensing means and to said
first connecting means, means located within said first connecting
means for controlling the flow of washing fluid from said storage
means to said dispensing means and means located within said second
connecting means for controlling the flow of gas from said storage
means to said dispensing means and to said first connecting means
whereby depending upon the condition of said pair of controlling
means either said washing fluid flows through said dispensing means
or said gas flows through said dispensing means and said pair of
connecting means.
2. A window wash system for inflight cleaning of aircraft windows
as defined in claim 1 further comprising a drain connected to said
controlling means located within said first connecting means.
3. A window wash system for inflight cleaning of aircraft windows
as defined in claim 2 wherein said controlling means located within
said first connecting means comprises a pump and a valve, whereby
said valve in one position permits the flow of the wash fluid from
said storage means into said first connecting means and blocks said
drain while said valve in second position prevents the flow of wash
fluid from said storage means into said first connecting means and
opens said drain.
4. A window wash system for inflight cleaning of aircraft windows
as defined in claim 3 further comprising means for regulating the
pressure of said gas within said storage means.
5. A window wash system for inflight cleaning of aircraft windows
as defined in claim 4 wherein said controlling means located within
said second connecting means comprises a valve, which at the time
said valve in said first connecting means is in said one position
prevents the flow of gas from said storage means into said
dispensing means and said first connecting means, and, at the time
said valve in said first connecting means is in said second
position permits the flow of gas from said storage means into said
dispensing means and said first connecting means.
6. A window wash system for inflight cleaning of aircraft windows
as defined in claim 5 further comprising means located within said
storage means for heating said washing fluid.
7. A window wash system for inflight cleaning of aircraft windows
as defined in claim 6 further comprising a means located within
said storage means for regulating said heating means.
8. A window wash system for inflight cleaning of aircraft windows
as defined in claim 7 wherein said dispensing means comprises a
first and second nozzle.
9. A window wash system for inflight cleaning of aircraft windows
as defined in claim 8 further comprising means located within said
first connecting means for regulating the flow through said first
nozzle and means located within said second connecting means for
regulating the flow through said second nozzle.
10. A window wash system for inflight cleaning of aircraft windows
as defined in claim 9 wherein said washing fluid is water.
Description
BACKGROUND OF THE INVENTION
This invention relates generally to window wash systems, and more
particularly, to an inflight window wash system for aircraft.
Many problems arise when it becomes necessary during flight to
satisfactorily remove dirt and insects from the window surfaces of
aircraft. For example,
A. THE WASH FLUID MUST BE CAPABLE OF PERFORMING WELL EVEN AT
EXTREMELY LOW TEMPERATURES SUCH AS -65.degree.F;
b. the wash fluid tank must be capable of operating at high
altitudes (low ambient pressure) thereby preventing boiloff of the
wash fluid;
C. A GREAT FORCE MUST BE APPLIED TO THE WASH FLUID TO INCREASE ITS
EFFECTIVENESS; AND
D. THE ENTIRE SYSTEM MUST BE CAPABLE OF OPERATING IN THE PRESENCE
OF HIGH SPEED AIR VELOCITIES ENCOUNTERED DURING FLIGHT.
Up to the present time although many window wash systems have been
utilized, none of these systems have overcome all the above
mentioned problems in an economical and high reliable manner.
SUMMARY OF THE INVENTION
The instant invention is a window wash system capable of use in the
inflight washing of aircraft windows and which alleviates the
problems set forth in detail hereinabove. Although the window wash
system is primarily designed for the inflight cleaning of Forward
Looking Infra-Red (FLIR) and Steerable Television (STV) turret
windows it is easily adaptable to all aircraft windows as well as
windows in general.
The window wash system of the present invention incorporates
therein a window wash pump which supplies hot
(135.degree.-155.degree.F) wash water at a nominal pressure of 500
psig. The wash water flows from the pump through a filter into two
spray nozzles for either FLIR or STV turret window wash. Washing is
accomplished by the impact of the high pressure spray on the window
surface while the window is driven past the nozzles by rotation of
the turret. It should be noted, however, that in use with
stationary or fixed windows, the nozzles of this invention may be
mounted on moveable or rotatable platforms.
After completion of a wash cycle, the wash valve and bleed air
valve open and the wash selector valve returns to the pump-to-drain
position. Pressurized low temperature bleed air is then piped from
the cabin air conditioning pack to the air pressure regulator. The
air pressure is reduced by the regulator and piped to the water
tank heat exchanger where the air is warmed to wash water
temperature. The warmed air passes through the bleed air valve to
purge the window wash system for prevention of freezing damage
after each was operation.
It is therefore an object of this invention to provide a window
wash system capable of cleaning the windows of aircraft during high
speed flight.
It is another object of this invention to provide a window wash
system which provides window wash fluid at a warm temperature.
It is a further object of this invention to provide a window wash
system which eliminates the boil-off of window wash fluid at high
altitude.
It is still another object of this invention to provide an inflight
window wash system for aircraft which is highly reliable in
operation, economical to produce and which utilizes conventional,
currently available components that lend themselves to standard
mass producing manufacturing techniques.
For a better understanding of the present invention together with
other and further objects thereof, reference is made to the
following description taken in connection with the accompanying
drawing and its scope will be pointed out in the appended
claims.
DESCRIPTION OF THE DRAWING
FIG. 1 is a schematic illustration of the inflight window wash
system of this invention showing the FLIR window wash cycle;
FIG. 2 is a schematic illustration of the inflight window wash
system of this invention showing the STV window wash cycle; and
FIG. 3 is a schematic illustration of the inflight window wash
system of this invention showing the system purge cycle.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
Reference is now made to FIGS. 1-3 of the drawing which show in
various modes of operation the window wash system 10 of this
invention. As pointed out hereinabove the window wash system 10 of
the instant invention is designed primarily for the cleaning of the
Forward Looking Infra-Red (FLIR) and Steerable Television (STV)
turret window 12 and 14 respectively. However, window wash system
10 is also capable of inflight cleaning of all windows of a high
speed aircraft.
The turret window wash system 10 of this invention utilizes a
pressurized tank 16 for storing the window wash fluid 18. The
window wash fluid 18 may be any suitable solvent, however, best
results are obtained when water is used as the fluid. Water leaves
no greasy residue, is non-flammable and is an effective fluid for
insect removal. Although water does have the disadvantage of a high
freezing point and a relatively high vapor pressure at operating
temperature, the other fluids with a more satisfactory freezing
point and vapor pressure have one or more of the disadvantages of
flammability, greasy residue or ineffectiveness for insect removal.
Since water proved to be the most satisfactory fluid, window wash
system 10 of this invention includes therein provisions for heating
and pressurization to prevent freezing and vaporization
respectively.
Water 18 enters tank 16 through a filler cap and safety valve 19.
In addition, tank 16 contains a conventional blanket heater 20
therein in order to heat the tank water 18 to a nominal temperature
range of 135.degree. to 155.degree.F. This temperature range is
more efficient for insect removal than water temperature just above
freezing. The water temperature is thermostatically controlled by
any suitable switching arrangement 22. For example, a plurality of
bimetallic switches can be utilized to operate the heater in such a
manner as to maintain the water temperature between 100.degree. and
170.degree.F.
Also operatively connected to tank 16 is an air pressure regulator
24. Pressurized low temperature bleed air (indicated by arrow 26)
is piped from the cabin air conditioning pack 27, for example, to
air pressure regulator 24. The air pressure is reduced by regulator
24 and fed through pipe 28 to water tank heat exchanger 30 where
the air is warmed to wash water temperature and remains within tank
16 until use thereof at a later time in a manner to be explained
hereinbelow.
A pair of lines or pipes 32 and 34 connect air 26 and water 18 to a
pair of nozzles 36 and 38. Interconnecting lines 32 and 34 is
conduit 40. Nozzles 36 and 38 are located adjacent STV window 14
and FLIR window 12, respectively. It should be noted that although
only two such nozzles are shown any suitable number may be used
with this invention. In addition, if desirable, the windows 14 and
12 may remain fixed while nozzles 36 and 38 are mounted on
conventional rotatable or slideable mountings.
Contained within line 32 are a pair of conventional valves such as
an electrically controlled STV wash valve 42 and an electrically
controlled bleed air valve 44. Located within line 34 are a pair of
suitable valves such as electrically controlled FLIR wash valve 46
and electrically controlled wash select valve 48. Adjacent valve 48
and also located with line 34 is any suitable pump 50 which moves
the fluid 18 during the window wash operation of system 10.
Window wash pump 50 supplies hot (135.degree.-155.degree.F) wash
water 18 at a nominal pressure of 500 psig to the two spray nozzles
36 and 38 for either STV or FLIR turret window wash. The electric
wash selector valve 48 operates in either of two positions. When
valve 48 is in the open position as shown in FIGS. 1 and 2 wash
water 18 flows from tank 18 through wash water inlet line 49 to
pump 50, while line 51 to overboard drain 52 is closed. Low
temperature bleed air 26 flows continuously through pump 18 to the
overboard drain 52 when wash select valve 48 is in the closed
position and bleed air valve 44 is in the open position as shown in
FIG. 3. The electrically controlled FLIR wash valve 46 closes to
block wash water flow to the FLIR turret nozzle 38 when the STV
turret wash cycle is in operation as shown in FIG. 2. STV wash
valve 42 closes to block wash water flow to the STV turret nozzle
36 when the FLIR turret wash cycle is in operation as shown in FIG.
1. When either FLIR or STV wash cycles are in operation bleed air
valve 44 closes to prevent wash water flow into the bleed air
supply line 54.
MODE OF OPERATION
Reference is now made to FIGS. 1-3 for the operation of window wash
system 10 of this invention.
In operation wash water 18 flows from tank 16 through line 49 to
pump 50 by passing through an open wash select valve 48. As seen in
FIGS. 1 and 2 of the drawing when wash select valve 48 is in the
open position bleed air valve 44 and line 51 to drain 52 is closed.
The wash water 18 flows from pump 50 at a nominal pressure of 500
psig into either spray nozzle 36 or 38 depending upon which valve
42 or 46 is in the open position as set forth hereinabove. Washing
is accomplished by the impact of the high pressure spray on the
window surface while windows 12 and 14 are driven past nozzles 36
and 38 by rotation of the turret (not shown). The time for a wash
cycle is nominally 30 seconds.
After completion of a wash cycle, the wash select valves 42 and 46
and the bleed air valve 44 open while the wash selector valve 48
closes inlet line 49 and opens line 51 leading to drain 52 as shown
in FIG. 3. Pressurized low temperature bleed air 26 is then piped
from the cabin air conditioning pack 27 to air regulator 24. The
warmed air 26 passes through the bleed air valve 44 to purge the
window wash system 10 for prevention of freezing damage after each
wash operation. Bleed air 26 flows through the window wash system
10 continuously unless the cabin air conditioning system is shut
down. It should be noted, however, that if desired the bleed air
may be furnished from an independent source. Another function of
bleed air 26 is to pressurize the vapor space in water tank 16 for
prevention of water boil-off at high altitude. Positive pressure is
also provided at the pump inlet line 49 to prevent cavitation.
The high velocity water jets emanating from nozzles 36 and 38 make
it possible to use this type of system in the presence of high
speed air velocities encountered in flight. High-speed air
velocities are not a major problem in the FLIR and STV turret
windows since the window wash operation is accomplished with the
windows facing aft and the nozzle spray protected by fairings
located directly behind the FLIR and STV turrets. Nevertheless,
system 10 of the present invention is also applicable to inflight
washing of aircraft windshields where high velocity airstreams
would otherwise be a problem.
Although this invention has been described with reference to a
particular embodiment, it will be understood to those skilled in
the art that this invention is also capable of a variety of
alternative embodiments within the spirit and scope of the appended
claims.
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