US3077779A - Air sampling means - Google Patents

Air sampling means Download PDF

Info

Publication number
US3077779A
US3077779A US7955A US795560A US3077779A US 3077779 A US3077779 A US 3077779A US 7955 A US7955 A US 7955A US 795560 A US795560 A US 795560A US 3077779 A US3077779 A US 3077779A
Authority
US
United States
Prior art keywords
vessel
air
sample
altitude
liner
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US7955A
Inventor
Harold E Froehlich
Roger A Kizzek
Donald F Melton
Richard L Schwoebel
Original Assignee
Harold E Froehlich
Roger A Kizzek
Donald F Melton
Richard L Schwoebel
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Harold E Froehlich, Roger A Kizzek, Donald F Melton, Richard L Schwoebel filed Critical Harold E Froehlich
Priority to US7955A priority Critical patent/US3077779A/en
Application granted granted Critical
Publication of US3077779A publication Critical patent/US3077779A/en
Anticipated expiration legal-status Critical
Application status is Expired - Lifetime legal-status Critical

Links

Images

Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01NINVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N1/00Sampling; Preparing specimens for investigation
    • G01N1/02Devices for withdrawing samples
    • G01N1/22Devices for withdrawing samples in the gaseous state
    • G01N1/2273Atmospheric sampling
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01NINVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N1/00Sampling; Preparing specimens for investigation
    • G01N1/02Devices for withdrawing samples
    • G01N1/22Devices for withdrawing samples in the gaseous state
    • G01N1/2273Atmospheric sampling
    • G01N2001/2279Atmospheric sampling high altitude, e.g. rockets, balloons

Description

Feb. 19, 1963 H. FROEHLICH ETAL 3,

' AIR SAMPLING MEANS Filed Feb. 10, 1960 3 Sheets-Sheet 1 1514x0121; z". morillzl m R061??? A, KIZZ 302K410 E MELTO fizzy ATTORNEY F b 19 19 3 H-v E. FROEHLICH ETAL 3 077 779 AIR SAMPLING MEANS Filed Feb. 10, 1960 5 Sheets-Sheet 2 '55 52 64 l K0dEKA.7ZZEK,

ATTORNEY 19, 1963 H. E. FROEHLICH ETAL 3,077,779

AIR SAMPLING MEANS Filed Feb. 10, 1960 5 Sheets-Sheet 3 rrq; 6'.

F mamzrmmim; IUU 9 Roam Airzzzza INVENTORS ATTORNEY ttes This invention relates to the sampling of high altitude atmospheric air.

It is an object of the invention to provide improved apparatus and technique for collecting an uncontaminated air sample at high altitude ambient pressure and bringing the sample to earth, where the sample may be conveniently analyzed.

Another object is to collect a relatively large air sample at the collection altitude and ambient pressure in a large container, transfer the sample to a relatively small container capable of withstanding ground impact and abrasion, and deliver the latter container intact to earth.

A further object is to provide an improved container for delivering the sample to earth.

Additional objects and advantages of the invention will appear as the description proceeds.

The invention will be better understood on reference to the following description and the accompanying more or less schematic drawing, wherein:

FIG. 1 shows a balloon system embodying features of the invention, just as it is launched or in an early stage of its ascent.

FIG. 2 shows the system at ceiling altitude just as the collection of the sample has been completed.

FIG. 3 shows the descending system when the sample has been completely transferred to the delivery vessel shortly before ground impact.

.FIG. 4 shows circuitry for controlling the various squibs, valves, and blowers.

FIG. 5 is an elevational view taken at 5--5 in FIG. 4.

FIG. 6 is a fragmentary elevational view of a tube from which the liner of the delivery vessel may be formed.

FIG. 7 is a fragmentary elevational view of a tube from which the middle or outside layer of the delivery vessel may be formed. FIG. 8 is a view, partly in section and partly in elevation, showing the delivery vessel as it appears when fully inflated, the seams and the gathering at the tops and hottoms of the three layers being omitted for the sake of simplicity. FIG. 9 is a fragmentary top plan view taken at 9-9 in FIG. 8 and showing the gathering of the material but omitting the seams.

FIG. 10 is an enlarged fragmentary sectional view taken at ill-10 in FIG. 9 to show the gathering of the material at the ends of the delivery vessel.

. Referring now more particularly to the drawing, disclosing an illustrative embodiment of the invention, there is shown at 10 a balloon system including a tow vehicle such as a balloon envelope 12 having a port 13 (FIG. 4) controlled as by a lift gas escape hatch l4 biased toward open position by a spring 16 but held closed by a cord 18 passing through a squib 20.

A load line 21 suspended from the envelope 12 passes through a squib 22 and in turn suspends a parachute 23. Suspended from the parachute 23 by a load line 24 is a discharge valve 25 secured as at 26 to the top of an inelastic flexible air sample delivery vessel or compartment 27 whose details will appear as the description proceeds. The ends of the vessel 27 are connected by a load support assembly 23 (FIG. 8) within the vessel. A housing 3,d77,779 Patented Feb. 19, 1963 29 secured as at 3!} to the bottom of the vessel 27 contains a transfer blower 31 (FIG. 4), preferably of the axial type, and a valve 32 comprising a gate 33 biased by a spring 34 toward closed position but held open by a cord 35 passing through a squib 36. The housing 29 is connected at 37 to the top of an air sample collector or compartment such as the film bag 3S. A perforated hose $9 is suspended from the top of and extends a substantial distance down in the collector bag 38 to prevent the blower 31 from sucking the film material of the bag and thus to prevent interference with flow from the bag to the vessel 2'7. The hose 39 is of a character which may flex but will not collapse to the extent of shutting off flow therethrough.

A housing 4i) for a valve 41 is connected as at 42 to the bottom of the collector 38. The valve 41 comprises a gate 43 biased by a spring 4-4 toward closed position but held open by a cord 45 passing through a squib 46. A preferably centrifugal type collector blower 47 for driving the sample from the high altitude atmosphere into the collector 38 is connected as at 4-8 to the bottom of the housing 4%, and has an atmosphere inlet 50, providing a seat for the gate 51 of a valve 52, the gate being biased by a spring 53 toward open position but held closed by a cord 54 passing through a squib 55.

Suspended from the blower 47 as by a line 56 is a housing 57 for the power supply, squib and blower controls, and a radio beacon (not shown) enabling the system 10 to be tracked.

A low pressure aneroid bellows switch 60 has an arm 62 connected via battery 64 to ground and arranged to sweep over a strip 66 having a contact 68 connected to the squib 55 and also to a timer 7% having a grounded hand 72 adapted to complete a cycle in a predetermined period. The timer dial 74 has a contact 76v elongated in the direction of sweep of the hand 72 and connected via a battery v78 to the blower 47. Beyond the contact 76 in the-sweep of the hand 72, the dial 74 has a contact 30 connected via a battery 82 to the squib 46 and also to the squib 20.

A delayed double action high pressure aneroid bellows switch 86 has an arm 88 connected via a battery 90 to one terminal of the transfer blower 31 and is adapted to sweep over a strip 92 having a contact 94 connected to the other terminal of the blower. The arm 88 is also connected via the battery 90 to one terminal of the squib 36 whose other terminal is connected to a second contact 98 on the strip 92. As the balloon system 19 (FIG. 1) ascends, the arm 83 rides on a bar 100 which is attached at one end 102 at the low altitude end 104 of the strip 92; at an altitude above that at which engagement between the arm 88 and the contact 94 can occur, the arm will snap oil the free end 106 of the bar and onto the strip; thereafter the arm will ride along the strip and eventually, pursuant to descent of the system, successively engage the contacts 94 and 98.

The balloon load line squib 22 is connected in series with a battery 110 and a mercury switch 112.

The envelope 12 having been inflated to the extent 116C? essary to carry the system 10 at or approximately at the desired rate of climb and to the predetermined high ceiling altitude at which a sample of the atmosphere is to be cap tured, the system is launched. The inflation can be carried out in any suitable way known in the art. For this purpose, for example, the envelope 12 could be provided with an inflation tube 116 communicating at its upper end with the interior of the envelope, and the nozzle of a hose from a lift gas supply (not shown) introduced into the open lower end of the tube and then removed when inflation is stopped, whereupon the tube may be tied closed as at 118. At launching, the system 10 has the appearance shown more or less schematically in FIG. 1, the envelope 12 being slightly inflated (with its inflation bubble); the vessel 27 and the collector 38 evacuated and accordingly collapsed; the balloon envelope lift gas escape hatch 14, the discharge valve 25, and the collector blower inlet valve 52 being closed; the collector blower outlet valve 41 and the transfer blower valve 32 being open; the timer switch hand 72 being at its starting position (FIG. 4); the bellows arm 62 being at its ground altitude position (upper end portion of contact strip 66, FIG. 4); the bellows arm 88 being at its ground altitude position off the strip 92 and in engagement with the bar 100 near the strip end 104; and the mercury switch 112 being open (FIG. 4).

When the ascending system reaches a predetermined alitude which is slightly below ceiling (collection) altitude, the bellows arm 62 engages the contact 68 to close the switch 60, firing the squib 55 and thereby allowing the collector blower inlet valve 52 to open. Any air entering the collector 38 by virtue of the opening of the valve 52 will be of slight volume and will be so close in character to that of the air at collection altitude as to have no appreciable effect on the quality of the collected sample as a whole. If desired, the valve 52 could be opened when collection altitude is reached.

Closing of the switch 60 also starts the timer 70 and accordingly the hand 72. When a predetermined period has elapsed, the hand 72 reaches the contact 76, starting the collector blower 47. This period is ample to insure that the system 10 is at collection altitude when the blower 47 starts, as the rate of climb of a given balloon system cannot always be accurately predicted.

The collector blower 47 proceeds to draw air from the ceiling altitude atmosphere and drive the air into the collector bag 38. The hand 72 continues in engagement with the contact 76 for a sufficient length of time to enable the bag 38 to be filled with the desired volume of air at the ambient pressure. As a safety factor, the bag 38 is made oversize to preclude full inflation as otherwise the bag might burst.

When the desired volume of air has been collected in the bag 38 (FIG. 2), the hand 72 sweeps free of the contact 76, thus opening the circuit for the blower 47, which accordingly stops.

Promptly thereafter the hand 72 engages the timer contact 80, firing the squib 4-6, thus severing the cord 45, whereupon the collector bag inlet valve 41 snaps closed to prevent escape of the collected air sample from the bag 38. This engagement with the contact 80 also fires the squib 20, thus severing the cord 18, enabling the balloon envelope hatch 14 to spring open and thus allowing lift gas to escape from the envelope 12 through the port 13 and thereby initiate descent of the balloon system 10 and opening of the parachute 23. The rate of the descent will of course increase until the bottom level of the lift gas in the envelope 12 has risen to such an extent that no more of the lift gas will escape from the envelope port 13 (FIG. 4), whereupon the descent will stabilize at a predictable rate.

The contact 68 is of such extent along the strip 66 as to insure sustained engagement with the switch arm 62 at least until the hand 72 engages the contact 80. The port 13 is of predetermined size and location above the bottom of the envelope 12 to insure against so precipitate a drop from ceiling alitude as could operate to rupture the envelope, yet provide suflicient rapidity of descent to insure that the arm 62 will have separated from the low altitude end of the contact 68 so that the timer 70 will stop before the hand 72 can again reach the contact 76.

As the balloon system 10 descends, the captured air sample in the bag 38 is progressively compressed by the increasing ambient atmospheric pressure. Due to inertia, the natural tendency of the bag 38 to collapse, the dynamic pressure of the ambient air against the lower part of the bag, and the solar heat which warms and therefore tends to render the sample less dense than the ambient air, part of the sample is moved into the vessel 27, and the bag becomes increasingly slack.

With descent of the system 10, the switch arm 88, now riding on the strip 92 toward the low altitude end 104 of the strip, comes into engagement with the contact 94 at a predetermined lower-than-ceiling altitude, closing the circuit for and starting the upper blower 31, which proceeds to transfer additional sample air from the collector bag 38 to the vessel 27, thus further collapsing the bag. The arm 88 first engages the contact 94 at a sufiiciently high lower-than-ceiling altitude, and the altitude range of the contact and the stabilized rate of descent are such, that the engagement will continue until the vessel 27 is fully inflated while the system 10 is aloft (FIG. 3) and the air in the vessel is at a pressure of several inches of water to give the vessel a cylindrical shape. On disengagement of the arm 88 from the low altitude end of the contact 94, the circuit for the blower 31 is opened, stopping the blower, and the arm comes into engagement with the contact 98 to fire the squib 36 and thus sever the cord 35, enabling the spring 34 to close the valve 32 and thereby seal the air sample in the vessel 27. At this stage the system 10 is still aloft, although prefer-ably relatively close to earth.

The balloon system 10 continues its descent and, on impact of the housing 57 with the ground, the mercury switch 112 will tilt or tumble and close, closing the circuit for and firing the squib 22, thus severing the envelope 12 from the remainder of the balloon system. If this were not done, the envelope 12 would act as a sail on the ground and thus drag the remainder of the system along the ground. The discharge valve 25 can then be opened by a member of the ground crew or other person to enable the air sample to be removed from the vessel 27 for analysis.

The parachute 23 prevents overspeed of the final descent and also serves as a safety precaution to lower the load gently in the event of failure of the balloon vehicle 12. Th s factor is particularly important as the load could weigh up to or over 500 lbs.

. Since the bag 38 is not appreciably stressed in use, and

lightness in weight is desirable as noted above, it can be made of thin, light weight film without reinforcement and can be inexpensively constructed, for example of polyethylene or other suitable plastic or other film, and is therefore an expendable item. Accordingly, once having served its purpose, any damage which the collector 38 may undergo on impact or abrasion with trees, stones, or other ob ects, or the ground, is unimportant. Moreover, in order to contain an ample volume of air at the low pressure encountered at the collection altitude the bag 38 must be so large that reinforcing it to withstand impact and abrasion would add considerably more weight and expense than is involved with use of the delivery vessel 27, and would also render the system so bulky as to make launching more difiicult.

Inasmuch as the captured air sample must arrive uncontaminated, it is essential that the vessel 27 be made sufliciently rugged to withstand the rigors of ground impact and abrasion. Furthermore, to hold down the size and therefore the expense of the envelope 12 and the quantity of helium or other lift gas used, and the inflation time, and to facilitate launching, the load should be made as light in weight as is feasible, and this is a factor in the design of the vessel 27 as well as the collector 38, and the size and strength of the envelope. The vessel 27 in accordance with the invention is preferably so constructed that, when fully inflated, it takes the form of a cylinder preferably having a height equal to its diameter for optimum volume-to-weight ratio consistent with low manufacturing cost. A spherical shape would of course afford a maximum volume-to-weight ratio, but the difference is so small (about 22%) and the fabrication cost for a sphere so great compared to that for a cylinder that the cylinder having the aforementioned shape is much to be preferred.

The increase in weight of the system due to the addition thereto of the air sample will be offset by the buoyancy added by the sample, so that there will be no net increase in the weight of the system provided temperatures inside and outside remain equal.

Let it be assumed that an air sample which is to have a ground level volume of 1200 cu. ft. at ground atmospheric pressure is to be collected at an altitude of 80,000 ft., and that the transfer of the sample from the collector 38 to the vessel 27 is to be commenced when the system has descended to 30,000 ft. and completed at an altitude of 3000 ft. The collector 38 should then have a volumetric capacity of at least about 33,000 cu. ft, since that is the approximate volume of the sample at an altitude of 80,000 ft. The vessel 27 should have a volume of about 1300 cu. ft., since that is the approximate volume of the sample at an altitude of 3000 ft. For the purposes noted, the volume of the vessel 27 should be such that, when the blower 31 stops, the air in the vessel will be at a pressure slightly above the ambient pressure at 3000 ft.

For the example given, it would be suitable to arrange for the switch arm 62 to come into engagement with the contact 68 at an altitude of 75,000 ft.; the hand 72 to have a cycle of 60 minutes; a period of 20 minutes to elapse before the hand engages the contact 76; the hand to remain in such engagement for 30 minutes; the descent to stabilize at about 60,000 ft.; and the switch arm 88 to come into engagement with the contact 94 at an elevation of 30,000 ft. Of course, for this example, the switch arm 88 will come into engagement with the contact 98 when the system has descended to 3000 ft.

If the vessel 27 were rigid, the sample therein when sealed at 3000 ft. would arrive on the ground with its volume unchanged, so that the pressure of the sample in the vessel when at rest on the ground would be about 940 millibars, whereas the ambient pressure, if at sea level, would be 1013 millibars. The vessel 27 being collapsible, however, it will, when on the ground, confine the sample at essentially the ambient ground atmospheric pressure, so that the sample therein will be at the ground atmospheric pressure.

The vessel 27 preferably comprises an air-impervious inelastic flexible sheet liner 120, an air-pervious impact and abrasion resistant intermediate inelastic flexible sheet layer 122, and an air-pervious impact and abrasion resistant inelastic flexible sheet casing 124. A liner 120 of polyethylene film, having a thickness of 2 /2 mils, would be satisfactory. The layer 122 should be tough, and a rough nylon woven cloth, having a tensile strength of 100 lbs. per inch, would be suitable. The casing 124 is preferably a solar radiation-resistant impregnated cloth, for example a neoprene-impregnated nylon cloth, such as Fiberthin, or it could be of unimpregnated material such as the layer 122. Unless the layer 122 and casing 124 are air-pervious, air might be trapped in chambers between them or between either of them and the liner 120. Such air, expanding with ascent of the system 10, could rupture the vessel 27 and enter the interior of the vessel, thus contaminating the sample to be collected. The rupturing force and contamination could be substantial, consiclering the fact that at, say, a collection altitude of 80,000 ft., the trapped air would have or tend to have some 28 times the volume it occupied at ground level.

The liner 120 is formed of a tubular member 126 (FIG. 6) which may comprise rectangular panels 128 heat-sealed continuously throughout their lengths as indicated at 130. Each end of the tube is gathered, and the resulting central portion is wrapped about a metal or other suitable ring 132 (FIG. 8) and heat-sealed as at 134 in a continuous circle about the ring periphery. The load support assembly 28 comprises a suspension cable 136 linked as at 138 at each end to diametrically opposite eyes 140 having stems passing through the inner part of the liner portion and threaded into the ring 132.

The layers 122 and 124 are each formed from a tubular member (FIG. 7) which may consist of rectangular panels 6 stitched together throughout their lengths as at 142; Each end of the tubular member is gathered as in the case of the tube 126, in any suitable fashion such as indicated at 144 (FIGS. 9 and 10), but to provide a reduced end opening 146 (FIG. 8), and there stitched as at '148.

The casing 124 is equipped with a longitudinal zipper 152 (FIG. 8) providing apassage enabling the layer 122 to be assembled within the casing, and the layer 122 has a like zipper 154 positioned directly behind the zipper 152 to provide therewith a passage enabling the liner to be inserted into the layer 122. The stitching, particularly at 142 (FIG. 7), provides numerous passages through the casing 124 and layer 122, and the latter is air-pervious even aside from its stitching, so that the atmosphere is in free communication with the outside of the liner 120. The zippers 152 and 154 render the layers 122 and 124 additionally airpervious.

The rings 132 are formed with additional tapped holes (not shown) for the reception of the bolts 26 and 30, respectively.

As noted above, the vessel 27 is collapsible. However, when fully inflated, the vessel 27 assumes the cylindrical shape shown in FIGS. 3 and 8. The load support assembly 28 operates to insure that the vessel 27 will assume a cylindrical shape when fully inflated and to relieve the vessel from stress from the remainder of the load train.

The pair of layers 122 and 124 is preferred to a single thick outside layer because of the greater resistance to penetration by a thorn, barbed wire, or other sharp object. Such an object gaining entrance to a single thick layer will pass through to the liner more readily than will be the case if the object must enter a second protective layer. The fact that the protective layers 122 and 124 are not bound together in the manner of laminations promotes the resistance to penetration to the liner.

While preferred constructions and operations are herein described in some detail, they should not be regarded as restrictions or limitations, as many changes may be made in construction and arrangement of parts without departing from the spirit and scope of the invention.

We claim:

1. In an apparatus for sampling high altitude atmospheric air,

a flexible vessel adapted to be parachutcd to the ground;

said vessel having an opening at one end for the reception of an atmospheric air sample at high altitude; said vessel comprising an air-impervious inelastic flexible film liner;

said vessel also comprising flexible relatively tough envelope means secured to and embracing the liner for protecting the liner from rupture due to ground impact and abrasion;

the envelope means being air-pervious to preclude entrapment of air between the envelope means and the liner;

the envelope means being equipped with zipper means to enable the liner to be readily inserted in the envelope means preparatory to their securement;

the zipper means being air-pervious.

2. In an apparatus for sampling high altitude atmospheric air,

a flexible vessel adapted to be parachutcd to the ground;

said vessel having an opening at one end for the reception of an atmospheric air sample at high altitude; said vessel comprising an air-impervious inelastic flexible film liner;

said vessel also comprising flexible relatively tough envelope means secured to and embracing the liner for protecting the liner from rupture due to ground impact and abrasion;

the envelope means being air-pervious to preclude entrapment of air between the envelope means and the liner;

the envelope means being equipped with zipper means References Cited in the file of this patent UNITED STATES PATENTS Grimm May 5, 1959 8 Iewet't Sept. 29, 1959 Lewis Dec. 1, 1959 Melton July 5, 1960 Schwoebel Aug. 30, 1960 Yost Aug. 30, 1960 Smith Apr. 4, 1961

Claims (1)

1. IN AN APPARATUS FOR SAMPLING HIGH ALTITUDE ATMOSPHERIC AIR, A FLEXIBLE VESSEL ADAPTED TO BE PARACHUTED TO THE GROUND; SAID VESSEL HAVING AN OPENING AT ONE END FOR THE RECEPTION OF AN ATMOSPHERIC AIR SAMPLE AT HIGH ALTITUDE; SAID VESSEL COMPRISING AN AIR-IMPERVIOUS INELASTIC FLEXIBLE FILM LINER; SAID VESSEL ALSO COMPRISING FLEXIBLE RELATIVELY TOUGH ENVELOPE MEANS SECURED TO AND EMBRACING THE LINER FOR PROTECTING THE LINER FROM RUPTURE DUE TO GROUND IMPACT AND ABRASION;
US7955A 1960-02-10 1960-02-10 Air sampling means Expired - Lifetime US3077779A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US7955A US3077779A (en) 1960-02-10 1960-02-10 Air sampling means

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US7955A US3077779A (en) 1960-02-10 1960-02-10 Air sampling means

Publications (1)

Publication Number Publication Date
US3077779A true US3077779A (en) 1963-02-19

Family

ID=21729025

Family Applications (1)

Application Number Title Priority Date Filing Date
US7955A Expired - Lifetime US3077779A (en) 1960-02-10 1960-02-10 Air sampling means

Country Status (1)

Country Link
US (1) US3077779A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3355940A (en) * 1964-03-05 1967-12-05 Comminsariat A L En Atomique Device for the study of atomospheric layers
US3521493A (en) * 1965-09-21 1970-07-21 Commissariat Energie Atomique Devices for sampling air at high altitude
US3800590A (en) * 1972-12-26 1974-04-02 Gte Sylvania Inc Detachment apparatus for balloon borne equipment
EP0481888A1 (en) * 1990-10-18 1992-04-22 AEROSPATIALE Société Nationale Industrielle Device for protection and deployment of telescopic tube
US20080041171A1 (en) * 2006-08-15 2008-02-21 Tans Pieter P System and method for providing vertical profile measurements of atmospheric gases
US7341224B1 (en) * 2004-10-14 2008-03-11 Osann Jr Robert Miniature expendable surveillance balloon system
US20120228434A1 (en) * 2009-11-13 2012-09-13 Zero2Infinity, S.L. Pod for space or near-space flights
US20160368604A1 (en) * 2015-06-22 2016-12-22 Elwha Llc Systems and methods for drone marking of airborne materials
US10065739B2 (en) 2015-06-22 2018-09-04 Elwha Llc Systems and methods for drone tracking of airborne materials
US20180259429A1 (en) * 2017-03-07 2018-09-13 Alexander B. Adams Air sampling system

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2884978A (en) * 1957-05-15 1959-05-05 Bruce F Grimm Collapsible fuel tank
US2906125A (en) * 1956-08-15 1959-09-29 Jr Frank B Jewett Sampling device
US2915097A (en) * 1958-07-23 1959-12-01 Charles T Lewis Portable collapsible tank
US2943490A (en) * 1959-02-17 1960-07-05 Donald F Melton Air sampling device
US2950882A (en) * 1956-04-16 1960-08-30 Gen Mills Inc Balloon gondola
US2950881A (en) * 1956-04-16 1960-08-30 Gen Mills Inc Balloon and gondola assembly
US2978004A (en) * 1959-06-11 1961-04-04 Donald F Smith Swivel closure for rotatable containers

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2950882A (en) * 1956-04-16 1960-08-30 Gen Mills Inc Balloon gondola
US2950881A (en) * 1956-04-16 1960-08-30 Gen Mills Inc Balloon and gondola assembly
US2906125A (en) * 1956-08-15 1959-09-29 Jr Frank B Jewett Sampling device
US2884978A (en) * 1957-05-15 1959-05-05 Bruce F Grimm Collapsible fuel tank
US2915097A (en) * 1958-07-23 1959-12-01 Charles T Lewis Portable collapsible tank
US2943490A (en) * 1959-02-17 1960-07-05 Donald F Melton Air sampling device
US2978004A (en) * 1959-06-11 1961-04-04 Donald F Smith Swivel closure for rotatable containers

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3355940A (en) * 1964-03-05 1967-12-05 Comminsariat A L En Atomique Device for the study of atomospheric layers
US3521493A (en) * 1965-09-21 1970-07-21 Commissariat Energie Atomique Devices for sampling air at high altitude
US3800590A (en) * 1972-12-26 1974-04-02 Gte Sylvania Inc Detachment apparatus for balloon borne equipment
EP0481888A1 (en) * 1990-10-18 1992-04-22 AEROSPATIALE Société Nationale Industrielle Device for protection and deployment of telescopic tube
FR2668260A1 (en) * 1990-10-18 1992-04-24 Aerospatiale Device for protecting and releasing a telescopic tube.
US7341224B1 (en) * 2004-10-14 2008-03-11 Osann Jr Robert Miniature expendable surveillance balloon system
US20080041171A1 (en) * 2006-08-15 2008-02-21 Tans Pieter P System and method for providing vertical profile measurements of atmospheric gases
US7597014B2 (en) * 2006-08-15 2009-10-06 The United States Of America As Represented By The Secretary Of Commerce System and method for providing vertical profile measurements of atmospheric gases
US20120228434A1 (en) * 2009-11-13 2012-09-13 Zero2Infinity, S.L. Pod for space or near-space flights
US9180981B2 (en) * 2009-11-13 2015-11-10 Zero2Infinity, S.L. Pod for space or near-space flights
US20160368604A1 (en) * 2015-06-22 2016-12-22 Elwha Llc Systems and methods for drone marking of airborne materials
US10065739B2 (en) 2015-06-22 2018-09-04 Elwha Llc Systems and methods for drone tracking of airborne materials
US10086938B2 (en) * 2015-06-22 2018-10-02 Elwha Llc Systems and methods for drone marking of airborne materials
US20180259429A1 (en) * 2017-03-07 2018-09-13 Alexander B. Adams Air sampling system
US10330571B2 (en) * 2017-03-07 2019-06-25 Alexander B. Adams Air sampling system

Similar Documents

Publication Publication Date Title
US3412963A (en) Method and apparatus for supporting an object
US5860251A (en) Rapidly deployable fire-protection apparatus
US3463266A (en) Extensible escape slide
EP0277787B1 (en) Hyperbaric chamber
DE69919905T2 (en) Autonomous stratosphere air ship
US3749337A (en) Aerial sled
US3229517A (en) Aerological mapping arrangement
US6648272B1 (en) Airship
US2310017A (en) Emergency transmitter
US3034154A (en) Inflatable life-rafts
US4295438A (en) Rescue locator signal package
US5538203A (en) Ballonet system for a lighter-than-air vehicle
US3800715A (en) Bomb recovery and shield apparatus
US3860984A (en) Inflatable life raft escape slide
US2593432A (en) Automatically operated radio buoy
US6305641B1 (en) Super-pressured high-altitude airship
US7380750B2 (en) Method for lighter-than-air aircraft
US3132322A (en) Radiosonic buoys
US4787575A (en) Signal balloon device
US2486158A (en) Pneumatic kite
US3119617A (en) Self inflating ball
US5645248A (en) Lighter than air sphere or spheroid having an aperture and pathway
EP1591356B1 (en) System for controlling the lift of an aircraft
US8505847B2 (en) Lighter-than-air systems, methods, and kits for obtaining aerial images
GB1461303A (en) Blank to form all or part of a shock absorbing bag-like structure for passenger vehicles and method of making said blank