Transverse flow edge heat pipe

An edge situated in high speed flow of medium is cooled by a tubular heat pipe having a longitudinal axis situated parallel to the edge. The exterior surface of the evaporator section of the heat pipe forms the edge. The heat pipe contains a working fluid existing in both gaseous and liquefied states. Heat input along the edge evaporates working fluid in the liquid state located in the evaporator section, and the heat is transferred transversely across the longitudinal axis of the heat pipe by the flow of vapor to the condenser section. The vapor condenses in the condenser section and releases its latent heat of vaporization. The condensate flows to the evaporator section by means of wicks composed of capillary material. The heat released into the walls of the condenser section is transferred through the walls by conduction and into another heat transfer device, for example, an active cooling apparatus or the evaporator sections of abutting heat pipes of conventional tubular configuration.

BACKGROUND OF THE INVENTION 
1. Field of the Invention 
This invention relates to heat pipes, and more particularly to heat pipes 
for cooling an edge situated in high speed flow of medium. 
2. Description of the Prior Art 
The maximum temperatures on a hypersonic flight vehicle typically occur 
along the leading edges of its wings, fins and engine inlet lips, and the 
edges comprising its fuselage chines. A severe thermal trajectory, such as 
that for a re-entry into the earth's atmosphere, causes extreme 
temperature levels that could exceed the thermal-structural capabilities 
of such an edge. In addition, thermal stress in the edge is caused by 
large variations in the aerodynamic heating about the stagnation line. 
The shape of the edge has a direct influence on the aerodynamic performance 
of the airfoil or fuselage chine and, ultimately, the flight vehicle, with 
performance qualitatively increasing with a decrease in the radius of 
curvature of the edge. More particularly, a smaller edge radius increases 
the range of a vehicle because it increases the maximum lift to drag 
ratio; allows a higher Mach number at a lower altitude; and permits 
flatter adjacent surfaces, which are easier to fabricate and thus have 
lower tooling and manufacturing costs than more curved surfaces, as well 
as providing more usable interior volume. An added benefit of sharper 
edges on a military flight vehicle is a reduction in the vehicle's radar 
cross section and radar reflection. 
However, a reduction in the edge radius causes an increase in the maximum 
temperature experienced along the edge, and thus the advantages attendant 
to decreasing the radius cannot be obtained without augmenting the 
capability of the edge to withstand the accompanying increase in 
temperature. 
There are three generic means for protecting an edge from the effects of 
extremely high temperatures generated by aerodynamic heating during a 
re-entry trajectory: (1) constructing the edge of a refractory material; 
(2) covering the edge with a thickness of ablative material; and (3) 
employing apparatus to cool the edge. 
With regard to the refractory materials approach, there are a number of 
materials commonly considered: ceramics, carbon-carbon, graphites and 
columbium (also known as niobium) alloys. 
High temperature ceramics have a higher density than the other materials 
commonly used, and adversely affect the vehicle's performance because of 
added weight. Ceramics are also brittle, and thus susceptible to fracture 
by workmen during installation or vehicle maintenance. In addition, this 
characteristic renders the edge vulnerable to cracking from thermal shock, 
that is, a rapid change in temperature such as that occasioned when rain 
is encountered while the ceramic edge still retains the heat acquired 
during a severe thermal trajectory. Ceramics are also subject to local 
melting, with the liquefied material either running until solidifying on a 
cooler surface area, or being swept away by the slipstream. In either 
case, a surface irregularity on the edge is created which increases the 
drag and otherwise causes the aerodynamic properties of the edge to 
deviate from the design parameters. The latter consequence is of prime 
importance where the edge is located on a guided missile because it will 
adversely affect the missile's accuracy. 
Carbon-carbon and graphite are not susceptible to local melting, and 
otherwise maintain their structural integrity in a severe thermal 
environment, but must be coated with a hard durable covering such as 
silicon carbide because both materials sublimate when subjected to high 
temperatures in the presence of oxygen. Thus, even a minute flaw in the 
covering will result in the formation of craters during a thermal 
trajectory that will increase drag, cause the aerodynamic characteristics 
of the edge to deviate from their design parameters and, as the craters 
become larger, ultimately affect the structural integrity of the edge 
unless the edge is refurbished. In addition, graphite is very fragile and 
thus particularly susceptible to damage from workmen. 
Columbium (also known as niobium) alloys also require a coating because 
they will oxidize when exposed to oxygen at high temperatures, but at a 
much lower rate than the sublimation of carbon-carbon or graphite. Thus, 
should the coating be flawed, columbium will be subject to the same 
problems as carbon-carbon and graphite, but the degradation in aerodynamic 
performance will be substantially slower and not require the refurbishment 
of the edge for a number of missions. However, columbium alloys have a 
relatively high density and are very expensive, and thus considerations of 
weight and expense militate against their use. 
The common alloys of other refractory materials such as molybdenum, 
tantalum, and tungsten are similarly prone to oxidation at high 
temperatures, but are less desirable than the columbium alloys because 
they weigh and cost even more. 
Due to considerations of weight and expense, the internal structural 
members situated behind an edge are not designed to withstand temperatures 
anywhere near those experienced at the edge. For example, at 500.degree. 
F. a structural member made from an aluminum alloy will retain only 20% of 
its room temperature load bearing capability, whereas it is not uncommon 
for temperatures along a leading edge or fuselage chine of a hypersonic 
flight vehicle to exceed 3500.degree. F. In order to allow the internal 
structure to be constructed of relatively light and inexpensive material, 
thermal insulation is inserted in between the edge and the internal 
structure, and the members which support the edge from the internal 
structure are designed to prevent excessive heat from being conducted 
through them to the internal structure. The design of the support members 
is further complicated because they must withstand the thermal stress 
caused by the extreme temperature differential occurring between the edge 
and the internal structure, as well as the material fatigue that accrues 
with repeated missions. 
As the edge temperature increases, the weight of the required insulation 
increases along with the complexity of the design of the support members. 
Thus, it is more desirable to protect the edge with an ablative material 
or cooling apparatus rather than a refractory material because the former 
protects by maintaining the edge temperature at a relatively low level and 
thereby avoids the thermal design problems attendant to the extremely high 
temperatures experienced throughout edges made from refractory materials. 
Following the same reasoning, the advantages noted with respect to the 
weight of the insulation and complexity of the support members where an 
ablative material or cooling apparatus is used instead of a refractory 
material become even more pronounced when the higher temperatures caused 
by a sharper edge are considered. 
Ablators protect the underlying structure from the effects of high 
temperatures by absorbing the heat and ablating when a high heating rate 
is sustained, thereby transferring the heat into the ambient slipstream 
with the ablated material. The main drawbacks to this approach are that, 
due to the erosion inherent in its use, the edge must be refurbished with 
a new thickness of ablative material after every flight, and leading edges 
and surfaces aft of the ablating edge are subject to being damaged by 
abrasion from the particles of ablated material introduced into the 
slipstream. In addition, the aerodynamic performance of the edge and, 
ultimately, the flight vehicle suffers from the recession of the edge 
surface. Another problem of particular significance to a military 
application is the increased radar reflection occasioned by the dispersion 
of the ablated material throughout the flow field. 
The other solution to the problem of severe aerodynamic heating along an 
edge located in high speed flow of medium is to to provide a cooling 
apparatus. Active cooling devices, transpiration apparatus and heat pipes 
are examples of cooling apparatus that have been employed in such a 
situation. 
Active cooling is achieved by passing a coolant medium through pipes that 
run near the edge. The temperature along the edge is reduced by the 
transfer of heat from the edge to the circulating coolant medium, with the 
heat ultimately being rejected to a heat sink at another point in a closed 
loop. This approach requires the installation of a pressurized circulatory 
cooling system comprised of a pump, piping, coolant medium and a means to 
cool the coolant medium. Thus, attendant to the use of active cooling are 
considerations of space, expense, added weight and a source for the work 
necessary to operate the pump and cool the coolant medium. As the required 
work is typically obtained from the vehicle's engine, this solution 
adversely affects the engine's performance and increases fuel consumption. 
The reliability of the system is also a factor which bears consideration 
in view of the fact that a crack or fracture in the pressurized piping 
will result in a loss of the coolant medium and cause a complete failure 
of the system, a potentially catastrophic event given the severity of the 
thermal environment and the design function of the edge. 
A transpiration cooling system forces a relatively cool fluid to pass over 
or through the surface to be cooled and then exhausts the fluid into the 
ambient atmosphere, obtaining the transfer of heat from the surface by the 
mechanism of convection. If the fluid is in its liquid state, additional 
cooling can be obtained from the absorption of heat occurring with the 
evaporation of the liquid into its gaseous state. As this is typically an 
open loop system, it requires a reservoir of cool, pressurized fluid to 
carry away the heat, and thus has a finite cooling capacity. 
When used on a flight vehicle, the system includes a pressurized storage 
tank that must be refilled with cooling fluid before every flight, 
together with a series of valves and sensors necessary to avoid expelling 
more fluid than is required to maintain the desired surface temperature. 
The tank adds to the gross weight of the flight vehicle and it, as well as 
the valves and connecting tubing, must be routinely checked for leaks. A 
further drawback is manifest from noting that the area to be cooled 
usually requires a series of openings in it for the cooling fluid to pass 
through and exhaust into the slipstream. Although this has been done on a 
nose tip, such a design requirement makes this system very impractical in 
many potential applications. 
Heat pipes have also been used as a means of cooling an edge on a flight 
vehicle. Briefly, a heat pipe is a tube having closed ends and enclosing a 
working fluid and a longitudinal wick. One region of the heat pipe (the 
evaporator) receives a local heat input which is conducted through the 
wall of the pipe and into the wick lining the interior surface of the 
pipe. The heat is absorbed by evaporating liquid working fluid contained 
in the wick in the evaporator region of the pipe. Due to a pressure 
differential, the vapor flows to the relatively cooler region of the heat 
pipe (the condenser) where it condenses upon the wick, releasing its 
latent heat of vaporization. The heat is then conducted through the wick 
and walls of the condenser where it is rejected by radiation and/or 
convection into free space, or conducted into a relatively cooler area, 
thereby completing the transfer of heat from the point of input to either 
free space or a cooler area. The liquid condensate flows by capillary 
action through the wick to the evaporator, thereby completing the closed 
loop cycle and providing a constant supply of liquefied working fluid for 
evaporation. The rate at which a heat pipe can transfer heat from the 
input point, and therefore its overall cooling capacity, increases as the 
distance the vapor must travel between the evaporator and the condenser is 
reduced. 
Turning to the prior art pictured in FIG. 1, a plurality of adjacent 
parallel conventional heat pipes 15 are shown installed in edge 16, with 
edge skin 17 drawn in phantom. Edge 16 is situated in high speed flow of 
medium having local wind vector 18 and stagnating along line 19. 
Each conventional heat pipe 15 is contained within a rigid, longitudinal 
tube 20, and is curved along its longitudinal axis with its evaporator 
section 21 centered about its minimum radius of curvature, r, and located 
about stagnation line 19. Two condenser sections 22 lie on either side of 
evaporator section 21, and are located adjacent to cooler surfaces of edge 
skin 17. The wick (not shown) is situated along the interior surface of 
tube and runs between evaporator section 21 and condenser sections 22. 
Heat generated along edge 16 about stagnation line 19 is transferred by a 
working fluid (not shown) from evaporator section 21 to condenser sections 
22. The heat is conducted through the thickness of tube 20 to the edge 
skin 17 adjacent to condenser sections 22, where it is rejected by 
radiation and convection into ambient atmosphere 23. 
There are two problems with this approach firstly, due to bending limits 
for the high strength materials necessarily used in the manufacture of the 
heat pipe tubes, there is a lower limit on the radius of curvature, r, 
that can be manufactured without cracking or kinking tube 20, or without 
kinking the wick, and this limit, in turn, translates into a lower limit 
on the radius of edge 16 that can be cooled with conventional heat pipes 
15. The minimum radius of curvature is a function of the material used to 
make the tube, the diameter of the tube, and the tube wall thickness. As 
an example, a tube made of Hastelloy X (the trademark for a nickel base 
super alloy produced by the Union Carbide Corporation) having an outer 
diameter of 0.5 inch and a wall thickness of 0.015 inch has a minimum 
radius of curvature (to the center line of the tube), r, of approximately 
two inches. 
The second design problem encountered with the use of conventional heat 
pipes to cool edges is illustrated by FIG. 2, a front view of adjacent 
parallel conventional heat pipes 15. When the pipes are placed in abutment 
with each other, there is a gap between them which increases from the 
point of abutment to a maximum distance, g, at edge skin 17. Points on 
edge skin 17 located along a locus of mid-points of a particular gap, g, 
and lying near stagnation line 19 will realize a higher maximum 
temperature for any trajectory than the other areas of edge 16 that lie 
closer to a heat pipe. The gaps thus diminish the cooling effect of 
parallel heat pipes 15 because they serve to increase the maximum 
temperature that edge 16 must be designed and constructed to withstand. 
In order to reduce the effective edge radius otherwise required, parallel 
pipes 15 have been slanted as shown in FIG. 3. The slant angle is .phi., 
that is, the angle between the plane containing the longitudinal axis of a 
heat pipe 15 and a plane containing the lower section on edge skin 17. The 
conventional, unslanted, vertical heat pipes 15 have a .phi.=90.degree.. 
With the radius of curvature, r, of heat pipes 15 held constant at its 
minimum value, the effective edge radius is reduced as .phi. is decreased. 
However, as .phi. is decreased, the gap, g, between adjacent heat pipes 15 
along edge skin 17 increases from a minimum value for .phi. equal to 
90.degree., and causes an increase in the maximum temperature realized at 
the hot spots located at the mid-points of each gap, g, resulting from the 
increase in the distance between the respective mid-points and adjacent 
heat pipes 15. As the edge must be designed to withstand the highest 
temperatures occurring at any lateral point along it, the effect of 
increasing the gap, g, largely offsets the benefits derived from 
decreasing the effective edge radius by slanting the heat pipes For 
example, at .phi.=20.degree. the effective edge radius is cut in half, but 
the gap, g, between adjacent heat pipes 15 is tripled. 
Another approach has been to employ a heat pipe having a transverse cross 
sectional shape other than circular, for example, trapezoidal or 
rectangular, in order to decrease the gap between adjacent heat pipes. 
However, the fabrication of such non-circular shapes entails significantly 
more expense than a circular cross section In addition, pipes having 
non-circular cross sections are still subject to the limit of a minimum 
radius of curvature necessary to avoid kinking or cracking the tube or 
kinking the wick. Furthermore, as it is very difficult to specially 
fabricate non-circular tubes in a slanted configuration, such tubes must 
be installed in a vertical orientation and cannot be slanted to reduce the 
effective edge radius. 
SUMMARY OF THE PRESENT INVENTION 
The present invention is a tubular heat pipe for cooling an edge situated 
in high speed flow of medium. The edge is formed by the exterior surface 
of the tube containing the heat pipe, while the juxtaposed interior 
surface of the tube comprises the evaporator section of the heat pipe. The 
condenser section lies transversely across from the evaporator section, 
with both sections running the longitudinal length of the tube containing 
the heat pipe. 
Aerodynamic heating occurring along the edge is conducted to the 
evaporator, where it is absorbed by the evaporation of the working fluid 
and subsequently transferred transversely across the longitudinal axis of 
the heat pipe by the flow of vapor from the evaporator to the condenser. 
The vapor condenses along the wick lining the walls of the condenser and 
releases its latent heat of vaporization, with the condensate being 
returned to the evaporator by capillary action through diametrical and 
circumferential wicks. 
In order to prevent the failure of the entire system in the event the edge 
is punctured, the heat pipe of the present invention is divided by 
thermally conductive walls into a plurality of identical heat pipes that 
lie side by side. 
The condenser section of the edge heat pipe rejects the heat directly into 
the ambient atmosphere or into a thermally connected conventional heat 
transfer device. For example, the auxiliary device could be a series of 
leg heat pipes of conventional design having their respective evaporator 
sections abutting the condenser section of the edge heat pipe. Heat from 
the condenser section of the edge heat pipe is conducted into the 
evaporator sections of the leg heat pipes, where it is transferred by 
vapor flow to the respective condenser sections. The heat is then 
transferred by conduction to an adjacent, relatively cooler surface area 
of the vehicle skin where it is rejected into the ambient atmosphere. The 
heat pipe of the present invention provides a solution to the problem of 
aerodynamic heating generated along edges situated in high speed flow of 
medium that is less expensive and lower in weight than using a refractory 
material. Moreover, in direct contrast to the use of a refractory 
material, the heat pipe of the present invention keeps the maximum 
temperature on the edge cool enough to allow it to be constructed of 
relatively inexpensive and durable super alloys that do not require 
frequent periodic refurbishment; will not subject the edge to 
deterioration and variation in aerodynamic performance due to local 
melting or sublimation; and simplifies problems relating to the design of 
the structural members which support the edge from the internal structure, 
as well as the thermal insulation for the internal structure of the flight 
vehicle 
In contrast with employing an ablative material, the flight vehicle can be 
reused without requiring the refurbishment of its edges after every 
mission; edges and surfaces aft of the edges will not be eroded and 
damaged; and the reflected radar image of the vehicle will not be 
amplified. 
The present invention cools an edge without the adverse affect on engine 
performance and fuel consumption, the added weight, the considerable 
expense, and the continuous maintenance requirements of an active cooling 
system, while needing less space and performing with greater reliability. 
The present invention does not require the design of the edge of the flight 
vehicle to be modified to accommodate holes, nor does it have the further 
drawbacks of limited capacity, complexity and continual maintenance 
inherent to transpiration cooling systems. The heat pipe of the present 
invention provides a flight vehicle with the significant advantages of 
cooling its edges with a heat pipe, while allowing the vehicle to realize 
the increased performance and smaller radar reflection of a sharper edge 
heretofore unobtainable with a conventional heat pipe. These advantages 
are the product of a design which altogether avoids the longitudinal 
bending limits of conventional heat pipes which previously set a lower 
limit on the radius of the edge that could be accommodated. 
The heat pipe of the present invention is able to adequately transfer and 
reject the increased heat caused by a sharper edge by using a 
configuration which substantially reduces the travel distance for the 
vapor and the condensate between the evaporator and the condenser sections 
in comparison to the travel distance in conventional heat pipes In 
addition, as the heat pipe of the present invention is virtually 
contiguous along the length of the edge, the hot spots along the edge 
occasioned by the gaps between parallel, conventional heat pipes are 
eliminated. 
OBJECTS OF THE INVENTION 
An object of the present invention is to adequately and reliably cool an 
edge situated in high speed flow of medium. 
Another object of the present invention is to cool an edge situated in high 
speed flow of medium using an apparatus that is light, inexpensive and 
maintenance free. 
Yet another object of the present invention is to cool an edge on a flight 
vehicle situated in high speed flow of medium without requiring work from 
an engine. 
A further object of the present invention is to cool an edge situated in 
high speed flow of medium using apparatus that is durable and reusable 
after being subjected to severe aerodynamic heating. 
Another object of the present invention is to cool an edge on a flight 
vehicle situated in high speed flow of medium without eroding or otherwise 
damaging flight vehicle surfaces situated aft of the edge. 
Still another object of the present invention is to adequately cool an edge 
situated in high speed flow of medium without developing hot spots along 
the edge. 
Yet another object of the present invention is to cool an edge on a metal 
flight vehicle situated in high speed flow of medium by a means that 
allows the vehicle's radar reflection to be reduced. 
A further object of the present invention is to cool the leading edge of an 
airfoil or a fuselage chine situated in high speed flow of medium while 
allowing the airfoil or fuselage chine to exhibit constant, predictable 
aerodynamic characteristics. 
Still another object of the present invention is to maintain the 
temperature of an edge on a flight vehicle situated in high speed flow of 
medium at a relatively low level, and thereby: (1) allow the edge to be 
made from a relatively light and inexpensive super alloy; (2) allow the 
internal structure to be comprised of relatively inexpensive and light 
non-refractory material with a minimum of insulation in between the edge 
and the internal structure, and (3) provide for a minimum of complexity in 
the thermal design of the members supporting the edge from the internal 
structure. 
Other objects, advantages and novel features of the invention will become 
apparent from the following detailed description of the preferred 
embodiments of the invention when considered in conjunction with the 
accompanying drawings.

DESCRIPTION OF THE PREFERRED EMBODIMENTS 
Turning to FIG. 4, edge heat pipe 24, a preferred embodiment of the present 
invention, is shown installed in leading edge 25 of airfoil 26 and 
situated with its longitudinal axis lying parallel to leading edge 25. It 
is to be understood that edge heat pipe 24 is not limited to the 
illustrated application, but can be similarly used to cool the fuselage 
chine of a space vehicle or the lip of an engine inlet, among other 
applications. 
Tubular casing 28 contains edge heat pipe 24. The components of edge heat 
pipe 24 include evaporator 29, condenser 27, and a working fluid in the 
states of vapor 30 and fluid 31. Circumferential wick 32 and diametrical 
wick 33 are both thicknesses of capillary material, with circumferential 
wick 32 lining the interior sides of casing 28 and diametrical wick 33 
laterally extending from condenser 27 to evaporator 29 and bisecting 
tubular casing 28. A secondary heat transfer device (not shown) is located 
in space 34, and is in thermal contact with condenser 27. 
Leading edge 25 is comprised of the exterior surface of the section of 
casing 28 which contains evaporator 29 along its interior surface, and is 
situated in high speed flow of medium having local wind vector 35 (shown 
for a zero angle of attack) and stagnating along stagnation line 36. 
Aerodynamic heating is generated along leading edge 25 about stagnation 
line 36, and is conducted through casing 28 into evaporator 29. Fluid 31 
is contained in the section of circumferential wick 32 located in 
evaporator 29, and absorbs the heat in evaporating to form vapor 30. As 
condenser 27 is cooler than evaporator 29, there is a pressure 
differential between the two regions which causes vapor 30 to flow to 
condenser 27. 
Vapor 30 condenses in the section of circumferential wick 32 lining the 
interior wall of condenser 27, and releases its latent heat of 
vaporization into the capillary material and adjacent casing 28. The heat 
is conducted through casing 28 and rejected into a secondary heat transfer 
device located in adjacent space 34. The condensate, fluid 31, flows by 
means of circumferential wick 32 and diametrical wick 33 to evaporator 29, 
completing a closed loop cycle. 
The secondary heat transfer device can be conventional heat pipes, an 
active cooling system, or any other apparatus capable of transferring heat 
away from casing 28. 
Holes 37 are located in diametrical wick 33 to allow vapor 30 to flow 
between the upper and lower halves of tubular casing 28. This feature 
becomes significant when airfoil 26 assumes an angle of attack relative to 
local wind vector 35 because, under such a condition, stagnation line 36 
and the aerodynamic heating centered about stagnation line 36 will move 
away from the centerline of airfoil 26 (the position of stagnation line 36 
for the zero angle of attack shown in FIG. 4). Under such unsymmetrical 
heating conditions, the coolest part of condenser 27 will be in the half 
of tubular casing 28 opposite that of stagnation line 36 and will cause a 
substantial flow of vapor 30 between the halves of tubular casing 28 lying 
on opposing sides of diametrical wick 33. 
FIGS. 5 and 6 illustrate edge heat pipe 40, another preferred embodiment of 
the present invention. Edge heat pipe 40 abuts and is thermally connected 
to leg heat pipes 41, and is shown operationally installed in airfoil 42 
with the longitudinal axis of edge heat pipe 40 lying parallel to leading 
edge 43 of airfoil 42. Airfoil 42 is situated in high speed flow of medium 
having local wind vector 44 and stagnating along stagnation line 45. 
Edge heat pipe 40 is comprised of evaporator 46, condenser 47, and a 
working fluid in the states of liquid 48 and vapor 49, all contained 
inside of rigid, tubular casing 50. Evaporator 46 is located along the 
interior, concave surface of tubular casing 50, while leading edge 43 is 
formed by the exterior surface of tubular casing 50. Condenser 47 is 
located along the interior surface of aft heat pipe wall 51. 
Circumferential wick 52 is a thickness of capillary material lining the 
interior surface of tubular casing 50. Diametrical wick 53 is a thickness 
of capillary material bisecting leading edge heat pipe 40 and extending 
diametrically from the interior surface of aft heat pipe wall 51 to the 
interior surface of the section of tubular casing 50 which forms leading 
edge 43. Holes 54 are located in diametrical wick 53 to allow for the flow 
of vapor 49 under unsymmetrical heating conditions, that is, when the 
angle of attack is not zero. 
Each leg heat pipe 41 has a conventional tubular configuration, and each is 
comprised of rigid, closed tube 55 enclosing evaporator 56, condenser 57, 
wick 58 and a working fluid in the states of liquid 59 and vapor 60. Wick 
58 is a thickness of capillary material lining the interior surface of 
tube 55. 
The longitudinal end of leg heat pipe 41 which contains evaporator 56 abuts 
aft heat pipe wall 51 of edge heat pipe 40. In order to facilitate thermal 
conduction between them, the abutting surfaces should be flat, and the 
abutting walls as thin as the respective vapor pressures of edge heat pipe 
40 and leg heat pipes 41 will permit. Aft heat pipe wall 51 and the 
adjacent walls of leg heat pipes 41 can be integrally produced in order to 
further enhance thermal conductivity by eliminating any discontinuity and 
reducing the thickness of material between them. 
Aerodynamic heating occurs along leading edge 43 about stagnation line 45, 
and is transferred by conduction through tubular casing 50 into evaporator 
46. The working fluid typically used in applications where the working 
temperature of the heat pipe will be approximately 1800.degree. F., for 
example, sodium or lithium, will be frozen at room temperature, and thus 
in a solid state. After a start up period necessary to melt the frozen 
working fluid, heat is absorbed by the evaporization of liquid 48 
contained in the capillary material of circumferential wick 52 located in 
evaporator 46. 
Vapor 49 flows towards the relatively cooler region of condenser 47, where 
it condenses onto the wicking material of circumferential wick 52 and 
releases its latent heat of vaporization into aft heat pipe wall 51. The 
condensate, liquid 48, returns to evaporator 46 by means of 
circumferential wick 52 and diametrical wick 53, thus completing the 
closed loop cycle. 
With respect to each leg heat pipe 41, the heat released by the 
condensation of vapor 49 is conducted through the interface of aft heat 
pipe wall 51 and tube 55, into the relatively cooler region of evaporator 
56. After a startup period necessary to melt the frozen working fluid, the 
heat vaporizes liquid 59 located in wick 58 to form vapor 60, which flows 
towards the relatively cooler region of condenser 57. Upon reaching 
condenser 57, vapor 60 condenses into wick 58, releasing its latent heat 
of vaporization into the walls of condenser 57. The heat is then rejected 
by radiation and convection from the walls of tube 55 into ambient 
atmosphere 23. The condensate, liquid 59, flows through wick 58 to 
evaporator 56, thus completing the closed loop cycle for leg heat pipe 41. 
In essence, edge heat pipe 40 in conjunction with leg heat pipes 41 
transfers heat from leading edgte 43 to a cooler, larger surface area, 
that is, the exterior surface of tubes 55 adjacent to the region of 
condenser 57, where it can be rejected into ambient atmosphere 23. The 
overall heat transfer capacity of edge heat pipe 40 increases with the 
exterior surface area of tubes 55 available to reject heat intO ambient 
atmosphere 23. Thus its heat transfer capacity can be tailored to suit the 
anticipated thermal environment of airfoil 42 by selecting the appropriate 
length for leg heat pipes 41. 
If edge heat pipe 40 were to suffer a puncture anywhere along the span of 
leading edge 43, the working fluid would escape and leading edge 43 would 
be left without cooling means for the remainder of the flight. Thus, for 
purposes of reliability, edge heat pipe 40 is divided into a plurality of 
juxtaposed sections by a plurality of parallel, thermally conductive walls 
61 that are impermeable to the working fluid and oriented normal to the 
longitudinal, spanwise axis of tubular casing 50. The spanwise breadth of 
each section can be calculated by methods known in the art to ensure that 
adjacent sections are capable of transferring sufficient heat from a 
punctured section to keep the maximum temperature along leading edge 43 
below the critical value at which structural failure would occur. 
Reliability considerations also suggest that each juxtaposed section of 
edge heat pipe 40 be abutted by at least one upper leg heat pipe 41 and at 
least one lower leg heat pipe 41. 
Turning to FIGS. 7 and 8, edge heat pipe 62, another preferred embodiment 
of the present invention for cooling a pointed leading edge, is shown 
installed in airfoil 64 . 
Tubular casing 63 encloses edge heat pipe 62, and also comprises leading 
edge 65 of airfoil 64. Edge heat pipe 62 is comprised of evaporator 66, 
condenser 67, surface wick 68, center wick 69, and a working fluid in the 
states of vapor 70 and liquid 71. Surface wick 68 and center wick 69 are 
composed of a thickness of capillary material, with surface wick 68 lining 
the interior surfaces of tubular casing 63 and center wick 69 bisecting 
tubular casing 63 and extending from aft heat pipe wall 72 to the point of 
leading edge 65. Holes 73 are located in center wick 69. 
Leg heat pipes 74 have a conventional tubular configuration, and each is 
enclosed in a rigid tube 75 and is comprised of evaporator 76, condenser 
77, surface wick 78, and a working fluid in the states of liquid 79 and 
vapor 80. Surface wick 78 is composed of a thickness of capillary material 
and lines the interior surface of tube 75. 
The end of leg heat pipe 74 which contains evaporator 76 abuts aft heat 
pipe wall 72 of edge heat pipe 62, while condenser 77 is located in the 
opposite end of leg heat pipe 74. In order to facilitate thermal 
conduction between the two adjacent heat pipes and thereby maximize the 
heat transfer rate of edge heat pipe 62, the abutting walls are in flat 
abutment and as thin as the respective vapor pressures of edge heat pipe 
62 and leg heat pipe 74 will allow. A further improvement in thermal 
conductivity can be obtained by integrally producing aft heat pipe wall 72 
and the adjacent wall of leg heat pipe 74, to thereby eliminate any 
discontinuity as well as reduce the thickness of material between the two 
heat pipes. 
When situated in high speed flow of medium having local wind vector 81, 
aerodynamic heating is symmetrically generated about the point of leading 
edge 65 and is transferred by conduction through tubular casing 63 and 
into the region of evaporator 66. After a start up period required to melt 
the initially frozen working fluid, the heat is absorbed by the 
evaporation of liquid 71 into vapor 70. 
Due to the pressure differential between evaporator 66 and condenser 67, 
vapor 70 flows into the region of condenser 67, condenses into surface 
wick 68 lining the walls of condenser 67, and releases its latent heat of 
vaporization. The condensate, liquid 71, flows by means of surface wick 68 
and center wick 69 to evaporator 66, completing the closed loop cycle for 
edge heat pipe 62. 
The heat released by the condensation of vapor 70 is conducted through aft 
heat pipe wall 72 and the abutting wall of leg heat pipe 74, into the 
region of evaporator 76. Again, after a startup period necessary to melt 
the frozen working fluid, the heat conducted from edge heat pipe 62 
vaporizes liquid 79 into vapor 80, and is transferred by the flow of vapor 
80 into the relatively cooler region of condenser 77. Vapor 80 condenses 
into surface wick 78 lining condenser 77, and releases its latent heat of 
vaporization. 
The condensate, liquid 79, returns to evaporator 76 by means of surface 
wick 78, completing the closed loop cycle for leg heat pipe 74. The heat 
released into the walls of condenser 77 is conducted through the thickness 
of tube 75 and rejected by radiation and convection into ambient 
atmosphere 23, thereby completing the transfer of heat from leading edge 
65 into the heat sink comprised of ambient atmosphere 23. 
For reasons of reliability, previously discussed in detail with respect to 
edge heat pipe 40, edge heat pipe 62 may be divided into a plurality of 
juxtaposed, independently operating heat pipe sections by a plurality of 
parallel, thermally conductive walls 82 that are impermeable to the 
working fluid and oriented normal to the longitudinal axis of tubular 
casing 63. The breadth of each heat pipe section is calculable by methods 
known in the art to ensure that adjacent sections can transfer sufficient 
heat from a failed section to keep the maximum temperature along the 
section of leading edge 65 otherwise cooled by the failed section below 
the critical temperature at which structural failure could occur. 
With respect to both the upper and lower rows of leg heat pipes 74, leg 
heat pipes 74 are staggered so that parts of two leg heat pipes 74 abut 
each section of edge heat pipe 62. Thus, in the event of the failure of a 
section of edge heat pipe 62, the abutting two leg heat pipes 74 can still 
contribute to the transfer of the additional heat load carried by the 
sections of heat pipe 62 adjacent to the failed section. This 
configuration will improve the overall performance of edge heat pipe 62 in 
the event of the failure of a section of heat pipe 62 in comparison to the 
unstaggered, one leg heat pipe to one edge heat pipe section configuration 
illustrated in FIG. 5. 
FIGS. 9, 10, 11, and 12 illustrate edge heat pipe 83, another preferred 
embodiment of the present invention, installed in fuselage chine 84 of 
space vehicle 85. 
Tubular casing 86 encloses edge heat pipe 83, and is comprised of concave 
wall 87 and flat aft wall 88. The exterior surface of concave wall 87 
forms fuselage chine 84 of space vehicle 85. 
Edge heat pipe 83 is comprised of condenser 89, evaporator 90, surface wick 
91, and a working fluid in the states of liquid 92 and vapor 93. 
Evaporator 90 is located along the interior surface of concave wall 87. 
Condenser 89 is situated along the interior surface of flat aft wall 88. 
Surface wick 91 is a thickness of capillary material lining the inner 
surface of tubular casing 86. 
Leg heat pipe 94 is enclosed within closed tube 95 and is further comprised 
of evaporator 96, condenser 97, wick 98, and a working fluid in the states 
of liquid 99 and vapor 100. Wick 98 is a thickness of capillary material 
lining the interior surface of tube 95. 
An end of tube 95 is in abutment with flat aft wall 88 of tubular casing 
86. The abutting walls are in flat abutment and each is as thin as the 
respective vapor pressures of edge heat pipe 83 and leg heat pipe 94 will 
permit, in order to facilitate thermal conduction between the two heat 
pipes and thereby maximize the heat transfer rate of edge heat pipe 83. 
Evaporator 96 is located in the end of leg heat pipe 94 which abuts flat 
aft wall 88, and condenser 97 is located in the opposite end. A further 
improvement in the thermal conductivity between heat pipe 83 and leg heat 
pipe 94 can be obtained by integrally producing flat aft wall 88 and the 
adjacent wall of leg heat pipe 94, thereby eliminating any discontinuity 
as well as reducing the thickness of material between the two heat pipes. 
When situated in high speed flow of medium, aerodynamic heating is 
generated along fuselage chine 84 and is transferred by conduction through 
concave wall 87 of casing 86 into the region of evaporator 90. After a 
startup period necessary to melt the initially frozen working fluid, the 
heat is absorbed by the evaporation of liquid 92 into vapor 93. Due to the 
pressure differential between evaporator 90 and condenser 89, vapor 93 
flows into the region of condenser 89, where it condenses into surface 
wick 91 and releases its latent heat of vaporization. The condensate, 
liquid 92, flows by means of surface wick 91 to evaporator 90, completing 
the closed loop cycle for edge heat pipe 83. 
The heat released by the condensation of vapor 93 is conducted through flat 
aft wall 88 and the abutting wall of tube 95 into evaporator 96 of leg 
heat pipe 94. Again, after a startup period necessary to melt the frozen 
working fluid, the heat conducted from edge heat pipe 83 is absorbed by 
the evaporization of liquid 99 into vapor 100. Due to the pressure 
differential between evaparator 96 and condenser 97, vapor 100 flows into 
the cooler region of condenser 97, where it condenses into wick 98 and 
releases its latent heat of vaporization. 
The condensate, liquid 99, returns to evaporator 96 by means of wick 98, 
completing the closed loop cycle for leg heat pipe 94. The heat released 
into the walls of condenser 97 is conducted through the thickness of tube 
95 and rejected by radiation and convection into ambient atmosphere 23. 
The length of leg heat pipes 94 is selected to provide the surface area 
necessary to reject the heat transferred from fuselage chine 84 into 
ambient atmosphere 23. 
As previously discussed with respect to edge heat pipe 40, edge heat pipe 
83 is divided into sections by a plurality of parallel, thermally 
conductive walls 101 that are impermeable to the working fluid and 
oriented normal to the longitudinal axis of tubular casing 86. The length 
of each section is calculated by methods known in the art to ensure that 
adjacent sections can provide sufficient cooling to keep the maximum 
temperature of a section of fuselage chine 84 otherwise cooled by a failed 
heat pipe section below the critical temperature at which structural 
failure could occur. Each of the juxtaposed sections of edge heat pipe 83 
is abutted by at least one leg heat pipe 94. 
Changes and modifications in the specifically described embodiments can be 
implemented without departing from the scope of the invention, which is 
intended to be limited only by the scope of the appended claims.