Free-fall body for obtaining wind velocity profiles by radar trackin

Stengel, R. F.

English

NASA Technical Reports Server

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REPLY TO 
ATTN OF: Gp 
TO 2 
N A T I O N A L  A E R O N A U T I C S  A N D  SPACE ADMf NlSTRATlON 
WASHINGTON. D.C. 20546 
Novembcr 6, 1970 
U. S .  Patent  No, .* n " 
. .  
Government or 
Corgorate E2nployee t 
Supplementary Corporate 
Source (if applicable) z 
NASA Pa ten t  Case No. 
https://ntrs.nasa.gov/search.jsp?R=19710006806 2020-03-17T02:37:12+00:00Z
April 21, 1970 R. F. STENGEL ~ , ~ Q ~ , ~ 5 ~  
WIND VELOCITY PROBING DEVICE AND METHOD 
4 Sheets-Sheet L Filed Jan. 24, 1966 
i 
! 
FIG. 1 
INVENTOR 
ROBERT F. STENGEL 
8 
4 Sheets-Sheet 2 
INVENTOR 
ROBERT E STENGEL 
BY 
April 21, 1970 R. F. STENGEL 3,507,150 
WIND VELOCITY PROBING DEVICE AND METHOD 
Filed Jan. 4 Sheets-Sheet 5 
8 
J 
.w 
t 
INVENTOR 
ROBERT F. STENGEL 
BY 
ATTORNEY 
April 21, 1970 R. F. STENGEL ,507,150 
W I N D  VELOCITY PROBING DEVICE AND METHOD 
Filed Jan. 24, 1966 4 Sheets-Sheet 4 
BY 
INVENTOR 
ROBERT F. STENGEL 
ATTORNEY 
ate 
parachutes which rely on the drag force for wind measure- 
A vertically dispensed trial of smoke can be photo- 
graphed at regular time intervals to determine the wind 
profile. Although the smoke trail method yields good data, 
it is too severely limited for prelaunch operational use 
when measurements can be made only under near-perfect 
visibility conditions during the daylight hours. Haze and 
clouds can obscure the smoke trail and the sun must be 
above and behind the photographic sites to assure good 
contrast between the smoke trail and the sky. Reduc- 
tion of the photographic data is a time-consuming process 
A method and apparatus for probing an altitude in- which presently cannot be completed qUiCwY enough to 
terval and obtaining profiles of wind velocities over the make the data useful in prelaunch operations. Another 
altitude interval including the release of a body having a 15 limitation is that a 1500-pound rocket is required to 
low frontal and high lateral projected area over the test carry enough chemical material to produce a smoke trail 
area and radar tracking of the body during its free-fall to 70,000 feet. 
descent to obtain indications of lateral deviations of the In order to overcome the disadvantages of the prior 
body from the vertical which is in turn a measure of the art, the instant invention contemplates use Of a light 
wind velocities a t  the various altitudes. 20 ballast weight, placed forward for aerodynamic stability, 
arid four large delta wings in cruciform arrangement. The 
skeletal structure of the wings is covered with aluminized 
Mylar film to provide a lifting and radar-reflective sur- 
The invention described herein was made by a former face. 
employee of the United States Government and may be It is an object of the instant invention to provide a 
manufactured and used by Or for the Government for 25 Sensor for rapidly measuring winds over a large altitude 
governmental purposes without the payment of any interval. royalties thereon or therefor. A further object of this invention is to provide a sensor 
The invention relates generally to a wind sensor and to make wind measurements in a minimum time period 
more particularly to a device for permitting obtaining ac- 30 of at least an order of magnitude greater than that of 
curate data as to wind direction and velocity. existing techniques. 
The launching of rockets or missiles involves various of the instant invention is to provide factors not the least of which is the wind profile along a wind presenting a minimum area to the vertical 
the ascent trajectory of the vehicle. Known wind sensors and yet which is sensitive to the horizontal 
include rising and falling balloons, falling “chaff’ and 35 of wind by presenting a maximum area to air currents in 
falling parachutes, all of which are radar reflective to the horizontal plane. 
facilitate radar measurement of the sensor’s path. These Still another object of this invention is to provide a 
sensors are used in conjunction with ground-based track- lifting having delta wings in cruciform arrange- 
ing radar sets which measure the vertical and horizontal ment with a ballast for proper orientation of the 
motion of the sensors. These motions are interrupted 
to  represent the wind velocity as a function of time and the foregoing and other objects are ac- 
altitude. All these sensors can be carried aloft by meteor- complished by utilizing a body having a ballast at 
ological rockets. In addition, balloons are frequently car- one end to which are pivoted the leading edges of the 
ried aloft by the buoyancy Of the helium they contain. delta wings. A flexible film of radar-reflective material 
Observance Of a smoke of 45 extends between the body and the wing leading edges to 
sensing wind direction and velocity. provide a sensor capable of rapid descent over a launch 
The primary disadvantage of presently used wind sen- The leading edges of the wings may be inflatable or 
sors is the time required t0 collect data in the altitude other deployment devices used for transfmming the 
region Of interest* take an hour and Sensor from a collapsed to a deployed configuration upon 
a half to traverse the from sea level to 90,000 50 the Occurrence of a predetermined event, such as reach- 
feet. Depending on the weight, height and to-area ratio, ing a specific altitude. 
parachutes and chaff reduce this time two-thirds. None A more complete appreciation of the invention and 
of the prior sensors traverses the altitude region quickly many of the attendant advantages thereof will be readily 
enough to give an instantaneous indication of wind at all apparent as the Same becomes better understood by 
altitudes. A secondary effect is that due to the time re- 55 reference to the following description when considered 
quired, these SenSorS travel far from the launch site and in connection with the accompanying drawings wherein: 
cannot be said to be sensing the winds in the area of im- FIG. 1 is a diagrammatic view of a payload incorpo- 
mediate interest. Chaff has the additional disadvantage rating the instant invention; 
that it disperses as it falls. The cloud of dipoles, packed FIG. 2 is a diagrammatic plan view of one embodi- 
closely at ejection, spreads to a very large size causing merit of the instant invention; 
a generally reduced radar return and searching of the FIG. 3 is a perspective view of the structural skeleton 
cloud by the radar, as the set automatically seeks the of an embodiment of the invention; 
strongest return. Eventually the cloud disperses and can FIG. 4 is a diagrammatic cross-sectional view of a 
no longer be tracked for wind data. mechanism for deployment of one embodiment of the 
hibit a tendency to “sail: that is, to have a horizontal FIG. 5 is a diagrammatic plan view of an alternative 
motion in the absence of winds. This is caused by the embodiment of fie invention; and 
flexible geometry of the sensor which in theory can FIG. 6 is a diagrammatic end view of the embodiment 
cause a normal, as well as a drag force. Whereas the of FIG. 5. 
normal force is in fact a desirable aspect of a lifting sen- 70 Referring now to the drawings and more particularly 
sor, its existence can be detrimental to balloons and to FIG. 1 wherein payload 60 is shown to include nose 
3,507,150 ment. 
WIND VELOCITY PROBING DEVICE 
AND METHOD 
Robert F. Stemgel, 41 Spring St., 
Princeton, N.J. 08540 
Piled Jan. 24,1966, Ser. No. 522,795 
Int. en. G O l W  1 /os 
I: US. C1. 73-189 
Another 
during descent. 
Provides another 
Parachutes and balloons are said to occasionally ex- 65 invention; 
3,507,150 
3 
cone 62 on the forward end of sensor container 64 and 
fin section 66 attached to the after end of container 64. 
A lifting sensor, generally designated numeral 
shown housed within container 64. 
FIG. 2 shows one embodiment of lifting sensor 10. 
Ballast nose 12 i s  of substantially projectile configura- 
tion and is rigidly attached to one end of body 14. 
llelta wipgs 18 extend outwardly from body 14 and 
are in a substantially cruciform arrangement. Leading 
edges 20 of wings 18 are made from a flexible, air-im- 
pervious material, such as Mylar, and are formed to  
deploy outwardly upon inflation. Leading edges 20 con- 
nect with inflator 30, a source of pneumatic pressure, 
which may be housed in the hollow ballast nose 12 and 
connected with leading edges 20 by any conventional 
conduits P6. Initiator 26 is associated with pneumatic 
supply sourGe 30 for activation thereof upon the occur- 
rence of a predetermined event, such for example, as 
attaining a prescrihed altitude or at a time signal. Acti- 
vation of inflator 50 causes leading edges 20 to deploy 
and stretch aluminized Mylar wing 24 to provide the 
cruciform configuration of lifting sensor 10. 
Referring to FIG. 3, wherein the structural skeleton 
of lifting sensor 10 is shown to include ballast nose 12 
attached to body 14 with leading edges 20 diverging rear- 
wardly from nose 12. Links 44 connect leading edges 
20 with body 14 and may be utilized in providing a 
rigid structure. For example, links 44 could be rigidly 
secured to  body 14 and leading edge 20 and lifting sen- 
sor BO would be of fixed configuration with wings 18, 
not fully shown, being at right angles to one another to 
provide the cruciform configuration. An alternative em- 
bodiment is contemplated wherein, for example, links 44 
would be spring members rigidly attached to body 14 
and pivotally connected to leading edges 20. Such a con- 
struction would automatically deploy upon ejection from 
a container. FIGS. 5 and 6 show another alternative 
embodiment of lifting sensor 10 wherein delta wings 18 
are canted to the longitudinal axis of body 14. This canted 
wing construction provides augmented stability by in- 
ducing spinning and thus a measure of gyroscopic sta- 
bility. 
FIG. 4 shows body 14 constructed of a tubular mem- 
ber rigidly secured to ballast nose 12 at one end. Me- 
chanical deployment device 28 includes rod 32 centrally 
located in body 14 and held in place by mounts 34. Ac- 
tuator 36 is of conventional construction and could uti- 
lize pneumatic or hydraulic pressure, mechanical springs, 
or electric motors and is connected to follower ring or 
annulus 38 which fits about rod 32. Arms 40 are rigidly 
secured to follower 38 and extend through slots 42 in 
body 14. As is readily apparent, slots 42 and arms 40 
are respectively perpendicular to  one another to provide 
the cruciform arrangement of wings 18 (not shown). 
Links 44 are pivotally connected to arms 40 and 46 and 
have the other end pivotally connected to bracket 50 
at pivot point 48. Brackets 50 are attached to leading 
edges 20 at a point such that when links 44 are fully 
extended, leading edges 20 will be fully deployed and 
wing material 24, connected to leading edges 20 and body 
14 in a conventional manner, will be stretched taut to 
provide stable wing forms. 
Upon the Occurrence of a predetermined event, initi- 
ator 26 activates actuator 36 which forces follower 38 
to ride along rod 32 and force arms 40 rearwardly of 
body 14 in slots 42. As arms 40 move rearwardly, links 
44 are caused to deploy and, through pivotal connections 
46 and 48, force leading edges 20 to pivot about pivot 
point 22 and expand fully. Although FIGS. 2 and 4 show 
deployment systems for the instant sensor, it is to be 
understood that any conventional system could be uti- 
lized; for example, the mechanism of FIG. 2 in United 
States Patent 3,197,158 issued to F. M. Rogallo on July 
27, 1965. 
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It is intended that the probe be carried to peak alti- 
tude by a meteorological rocket including payload 60. 
However, it is to be understood that many conventional 
means, such as balloons, are available for carrying sen- 
sor 10 to the pioper altitude. At peak altitudes, payload 
6(8 is released with fin section 66 being disconnected and 
lifting sensor 10 ejected from container 64. Once free 
of container 64, initiator 26 would be utilized to acti- 
vate deployment device 36 and thus cause expansion 
or deployment into the fully erected cruciform arrange- 
ment with ballast nose 12 orienting sensor 10 as it falls 
toward the earth. As its name implies, the lifting sen- 
sor derives its wind sensitivity from the lift force, rather 
than the drag force, provided by the relative air ve- 
locity. The sensor is a statically stable airplaine or  
missilelike Configuration possessing 120" or higher or- 
der rotational symmetry about its longitudinal axis. In 
the absence of wind, sensor 10 falls vertically wiith its 
longitudinal axis alined with the vertical due to its static 
stability. The cruciform configuration presents its min i  
mum arsa to the vertical for high fall velocity and its 
maximum area to the horizontal for high wind sensitivity. 
The chief advantage of the lifting sensor design of the 
instant invention is the short time required to collect 
wind data over a large altitude range. There are several 
gains to be obtained as a result in that the collected winds 
more nearly represent a vertical sampling of the winds 
at an instant of time. The reduced time required for a 
wind run allows persopnel and facilities to be free fnr 
other functions, resulting in a, substantial economic sav- 
ing and allowing increased freedom in aperation schedul- 
ing. The horizontal displacement of the probe will he 
much less than that of other sensors, thus allowing meas- 
urements of the winds more nearly above the launch sites. 
Further, the instant sensor maintains simplicity to pro- 
vide overall system reliability. 
Obviously, many modifications and variations of the 
subject invention are possible in the light of the above 
teachings. For example, an annular wing may be utiliged 
or the wings constructed of plural sheets for complete in- 
flation thereof. 
It is therefore to be understoqd tbat within the scope 
of the appended claims the invefftion may be practiced 
otherwise than as specifically described. 
What is claimed as new and desired to be secured by 
Letters Patent of the United States is: 
1. A lifting sensor comprising: a body member ballasted 
for orientation during flight; reflective means mounted on 
said body comprised of a plurality of delta wipgs arr9ngqd 
in a cruciform, extending from said body and having 
leading edges pivotally connected to said body, cQn- 
structed of a flexible air impervious material, with reflec- 
tive material attached to said body and said leading edges; 
a source of flqid pressure operatively connected with said 
leading edges; and means for activating said source, where- 
by said leading edges are extended to dispose said reflec- 
tive material so as to present a maximum area to hori- 
zontal wind components. 
2. A lifting sensor comprising: a body member bal- 
lasted for orientation during flight; reflective means com- 
prising a plurality of delta wings arranged in a cruciform 
and extending from said body, havipg leading edges pivot- 
ally connected to said body, with radar reflective mate- 
rial connected to said body and said leading edges; and 
means for deploying said leading edges comprising liqks 
having one end pivotally attached to sitid leadin8 edges 
and arms pivotally connected to ~e other end of said 
links; said deploywent means further including actuator 
means connected to move said arms and releasing means 
to control the actuator means, whereby said leading edges 
and the connected reflective material are deployed in 
response to activation of the releasing means. 
(References following page) 
3,507, I50 
References Cited OTHER REFERENCES 
UNITED STATES PATENTS Stone, I.: Early Infiatable Micrometeroid Paraglider 
Re-entry Tests Planned, from Aviation Week and Space 
Technology. Oct. 8, 1962, page 32. 1,243,542 10/1917 Moore _ _ _ _ _ _ _ _ _ _ _ _  244-3.27 2,494,026 1/1950 Anderson _ _ _ _ _ _ _ _ _  244-3.27 
2,938,681 511960 Palermo _ _ _ _ _ _ _ _ _ _ _ _  244-49 RICHARD c. QUEISSER, primary ~~~~i~~~ 1 3,340,732 9/1967 SCOgginS _ _ _ _ _ _ _ _ _ _ _ _  73-189 
J. W. MYRACLE, Assistant Examiner 
U.S. C1. X.R. FOREIGN PATENTS 
642,411 2/ 1937 Germany. 244-49 


Wind velocity probing device and method Patent

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