CA2140137A1 - Aerodynamically shaped probe - Google Patents
Aerodynamically shaped probeInfo
- Publication number
- CA2140137A1 CA2140137A1 CA002140137A CA2140137A CA2140137A1 CA 2140137 A1 CA2140137 A1 CA 2140137A1 CA 002140137 A CA002140137 A CA 002140137A CA 2140137 A CA2140137 A CA 2140137A CA 2140137 A1 CA2140137 A1 CA 2140137A1
- Authority
- CA
- Canada
- Prior art keywords
- barrel
- strut
- pressure sensing
- probe
- section
- 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.)
- Abandoned
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
- G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
- G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
- G01P5/165—Arrangements or constructions of Pitot tubes
Abstract
The present invention relates to an air data sensing probe that has a cylindrical barrel joined to a contoured strut section. The strut has leading and trailing edges formed along curved paths, and supports the cylindrical barrel at a position spaced from a mounting surface and facing upstream of relative air movement. The strut has a rounded leading edge, and is generally ogival-shaped in cross section. There is a blended, relatively quickly-changing transition section to blend the trailing end of the cylindrical barrel into the ogival-shaped strut section so that the probe has reduced weight of the strut and reduced drag, and through reduction of the cross-sectional area and rounding the strut leading edge, has enhanced anti-icing performance.
Description
W0~4/02858 ~14~37 PCI`/US93/06582 AERODYNAMICALLY SHAPED PROBE
R~CKGROUND OF T~F. I~vENTIoN
- The present invention relates to an air data sensing probe that is small in siæ to reduce weight while cnh~nçi~g aerodynamic pe,~u~lce.
s Strut-movnt~ probes for air data sensors have been utilized for years. There have also been probes which include curved tubes that have a forward-facing port for sensing pitot pl~Ul~, and curve laterally to the side and rearwardly to a molmti~ base or plate for mounting onto the side of a fuselage of an air vehicle. Such probes or air data sensing devices protrude from a o surface of an air vehicle, and thus will Inde~i~hly incl~ drag when Coul~;i with a similar vehicle without such p~l~us;on. Since strut-mo~nted probes are ~ to the air vehicle su~ce, l~l~U~ dislwbanc~s caused by the strut and ~ nt surface need to be co~ ~n~l~ in various ways. Strut-mounted probes also have to be heated for de-icing during use. The mass of the air data sensing device should also be minimi7~d.
Cylin~lrk~l barrel probes have been utilized for sensing pitot andlor static ~Jl~. Pitot ~JI~aUle iS scnsed tluuugh a forwardly facing port, while static ~Jl~IU~ iS sensed tluou~ op~n;.~g g~ne~lly ~ d;~-ul~- to the air flow. The strut on which the barrel is mount~ n~.~lly has a stre~mlined cross-section in fore and aft direction. Suitable strut l~;c~es~ has to be provided for de-icing heaters and also for carry~g ~e pl~Ul'~; signal cQndui or tubes.
It also has been lmown in the prior art to provide front and rear edges of air data sensor struts that are shaped in col~ d curves to ~n~ition from a folwa~dly-facing port to a side-mounting base for the air data sensor.
SU~M~RY OF l~F. INV~l~ON
The present invention relates to an air data sensor probe which can be for sensing pitot and/or static pl~s~ur~ that u~lizes a cylin-lric~l, forward-facing barrel having an open end for sensing pitot pleS~iUl'e. ~he barrel Wo 94/02858 2~ 37 Pcr/US93/06582 is ~up~l~d by a strut that curves rearwardly from the barrel and also laterally to a~Lch to a ...o...-~;ng base for ~~ E the air data sensor onto a ~ lg s~l~re The strut has div~ g front and rear edges that curve toward the ~o!~nl;ng base from the barrel. The strut is generally an ogival shape, with a s relatively rounded front edge which aids in C~e~ling ice, and thus reduces theamount of heat l~uucd during de-icing oper~tinn The barrel mounts to the strut with a support section that blends rapidly from cylin~ric~l to the ogival shape, using smooth surface conto~ to ~;ni...i~e drag. The air data sensing probe is small or compact and of low ~o weight when c~,np~ to other sensors in use, as well as being low in drag.
B~F nF-~cp~foN OF T~IF. nRAW~GS
Figure 1 is a top plan view of a s~rut - o~n~l air data sensor pr~be acco,~Llg to the present invention;
Figure 2 is a front elevational view of the device of Figure l;
Figure 3 is a ~ c lepr~ s~nl; ~;on of a top plan view of the device of Figure l;
Figure 4 is a s~ion~l view taken as on line 4--4 in Figure 3;
Figure S is a s~ion~l view ta~en as on line 5--5 in Figure 3;
Figure 6 is a ~ c-~ e view of the strut-mo~1nf~d air data sensor 20 probe made acco,ding to ~e present in-~lion.
D~TA~T Fn nF~ oN OF T~F p~2F.~-r l~RF.n F.MRODIM~
As shown in Figure 1, an air data sensing probe in~i~t~
genaally at 10 in Figure 1 i~l.d~s a crli.~ arrel por~on 12 that has an end opEni~ 14 facing toward the direction of air flow. The crlinti~ l barrel zs 12 is .no,~ d onto a strut se~ion 16, which in turn cu~es late~ally and r~dly from tbe ~ailing end of cylin~1n~l barrel 12, and late~ally from a central axis 18 of the cylin~lri~l barrel 12 toward a surface or sl~n 20 of an air -vehicle. The strut 16 has a mounting or plate base 22 that mounts to the air Wo 94/02858 ;2 14~37 PCI/US93/06582 vehicle in a convention~ cr. Generally, the outer side of the plate 22 is flush with the skin 20 so that drag is --;n;---;,~
As shown in Figure 2, the c~ d~ leading end opening 14 is across the entire intP.rn~ ~r of ~e barrel 12. The opening 14 fonns a 5 pitot pr~-llc sensing port facing in U~ ~lll direction to the air flow and is COl~t~ to sllit~hle tubing, not shown, within strut 16. The tubing has an end conn~ 13, which is joined to a suitable pl~'tUI~ sensor, not shown. The cylindrical barrel 12 is t~nCitinn~d to a g~onerally ogival cross-section shape of the strut 16 (as can be seen in Figures 4 and 5) in a short tr~ncition section 24 10 th~t smoothly blends the cylindrir~l shape of barrel 12 to the ogival cross-section of strut 16 in a ~ .. d;.l~ and ~.ill.oul having sharp or irregularedges. The cyli~ cAl ba~el 12 .-~ s a true ~lil-~.;~l sh~pe for a l length along its lo~tudin~ cis 18, which length is s~lbst~t;~lly equal to the tlict~nc~ b~.c~ thc placc of side surface 20 of the air vehicle and15 the barrel 12. The effec~ of the strut on air ~ in opc~g or port 14 is thus reduced to çnh~n~ re~iql ility of thc ~ gn~lc~
Tbe strut 16 itself has c4--~ curved front and rear (leading and tIailing) edges. A rounded (not sharp) leading edge 26.,~ ds ~b~ lly in a straight line ~djacrnt the air vehicle at a rcn~y inClin~d angle in~
zo at 28 ~ ,e to the air vehicle sur~cc 20. The leading edge 26 then curves at section 30 to ~ g~ lly joLn the outer surface of the ~lindlical barrel 12. The rear or traili;ng edge in~ t~d at 32 ~ ds at a gentle but dirf~ curve from the point where it joins the base 22 ~an the leading edge 26 folwa~ly and ouLw~u.]ly from the aircraft sldn 20 and base 22. The edges 32 and 26 converge 25 in direction toward the rear end of barrel 12, or, in other words, diverge indirection away from the barrel 12 bacl~ toward the base 22. A gentle, relativelylarge radius section 33 of the trailing edgè 32 blends into the outer surface ofthe cylindrical barrel 12.
WO 94~02858 PCI~/US93/06~82 ~a~7 As shown in Figure 2, the strut 16 also tapers in thicl~n~$5 along a central axis 35, which is shown generally in dotted lines at 34, so that the strut 16 is relatively thick or wide at its base portion 36 and reduces in size to a lateral ~;...~n~ on at 38 that is less than the 1i5~ r of the cylin~lric~l barrel s 12. Smoothly varying CG~ nd curved surfaces 39 are used for joining the strut 16 and the c~lind,i~al barrel 12. ~ef~ling to Figures 2, 3 and 6, the surfaces are srnoothly tapered to avoid irreg~ rities that will hlc~se drag or cause ~ul~ nl;zl air turb~ e On the upper surface of the strut 16, which is intli~t~ at 40, the tr~n~:ition section 24 has a bl~n~ surface 40A. The 10 blending surface 40A s~noothly enlarga in multiple directions from the surface 40, and enlarges to ~ .e c~l;nA~ l at about the line 46. This blending surfaoe also is d~igr~ to l~;n;~ f, drag wbile providing adequate ~U~ for the cylin~ fol w~ly di-~t~ barrel 12. A bottom surface 42 has a sirnilar enlarged surface bl~ ;~ to the cylin~lri~l barrel section 12, as shown in 42A
s in F;gure 6.
The sensor pr~>be 10 has heaters shown ~ ;~lly at 49 ln~t~ d in the strut 16 and also rnay have heaters in the barrel 12 for de-icing.
The heaters can be f~ '`'nGe heaters of conventional design. A suitable eonnr~Qr is-`shown at 50 in Figure 1 for el~ri~l c4/~nrcl;oll~ to the heaters 20 from the intc.iol of the air vehicle. The leading edge 26 of the strut 16 provides a r~undcd su~face tbat tends to shed ice. The rounded l~li~ edge 26 also provides an area for insertion of a r~ ~:c~n-~4 heater along and close to the edge 26 to increase the ~ s~ffi~p-ntly to melt or ie.llo~ the ice.
The ogival cross s~lion strut 16 is thin throughout its length to 2s reduce drag, and ~e quick ~nsition section 24 from the cylindrical or circular cross-section barrel 12 to a thin ogival strut section 16 is a smooth COlltOur~dsurface as well that tends to reduce weight, and decl~ drag. The transition section 24 extends in direction of axis 1~ prefe~bly in ~e range of one WO 94r02858 ~ 137 Pcr/US93/06582 ..ct~ r of the barrel 12. The tr~nCitio~ ~tio~C should be kept below two barrel ~i~m~ter in axial dir~tion.
The chord length to ll ;r~ s ratio, that is, the ~eral ~imPnciQn of the ogival cross s~tion indi~t~d at 26A in Figur~ 4 and 5 relative to ~e s chord ,easur~d from the leading to the trailing edges of the ogival strut and in~i~t~ at 26B, for eJtample, provides a st~ut that l~duces drag s~lb~ n and also ~ '5 the weight while providing adequate strength.
The ratio ~ the transverse ~ ;on 26A and the chordal on 26B may change s~l,sh r~ lly l~U'~UghoU~ the length of the strut 16.
0 In other words, ~lthough the strut 16 is ~inner where the chord length is shorter when "~u.~d normal to the cent~ is of the strut 16 the ~atio .~ g~s.
~lthough the ~ ~fid es 40A and 42A introduce a di~loc~tion in the flow, the blcn-l;ng area 24 ,~luccs this ~iclQ~ati~n~ The sulr~s of strut 16 areconve~ on the ~ .io- sides 40 and 42, as shown, and the walls of strut 16 are l~pt relatively thin. The ~du~ cross~ tion~l area of the strut 16 also enh~nC~s the anti-icing ~r~ Anc~. As previously stated, t_e effect of strut-induc~ ~ul~ enors on the .,.c~su~d pitot ~l~C opening 14 are also .eJu~. The ~I;nd. iC~l section of the barrel 12 provides for a large size pitot op~ning 14 relative to the ~ of the tube used.
- ~f~ling to Figure 3, a static p~, sensing port~~60 can be provided on the ~iyl;n~l~i~l barrel 12 at a desired loc~tiol- both as to annularposition around the barrel 12 and also lo~jtudin~l or a~ial positiol~ along the barrel 12. Usu~lly, the axis of the static sensing port is to the outer side of the probe and there Gm be two ports, one facing ~w~ly at about 60 from hGI ;7~ t 1 and the other dow--v/~dly also 60 from h.~ nl~l These a~es are shown at 60A in Figure 2. In such case, suitable plnmbin~ or tubing, not shown, is provided from the port 60 for carIying the static ~ u~ signals back through the strut 16 to the air vehicle.
.
R~CKGROUND OF T~F. I~vENTIoN
- The present invention relates to an air data sensing probe that is small in siæ to reduce weight while cnh~nçi~g aerodynamic pe,~u~lce.
s Strut-movnt~ probes for air data sensors have been utilized for years. There have also been probes which include curved tubes that have a forward-facing port for sensing pitot pl~Ul~, and curve laterally to the side and rearwardly to a molmti~ base or plate for mounting onto the side of a fuselage of an air vehicle. Such probes or air data sensing devices protrude from a o surface of an air vehicle, and thus will Inde~i~hly incl~ drag when Coul~;i with a similar vehicle without such p~l~us;on. Since strut-mo~nted probes are ~ to the air vehicle su~ce, l~l~U~ dislwbanc~s caused by the strut and ~ nt surface need to be co~ ~n~l~ in various ways. Strut-mounted probes also have to be heated for de-icing during use. The mass of the air data sensing device should also be minimi7~d.
Cylin~lrk~l barrel probes have been utilized for sensing pitot andlor static ~Jl~. Pitot ~JI~aUle iS scnsed tluuugh a forwardly facing port, while static ~Jl~IU~ iS sensed tluou~ op~n;.~g g~ne~lly ~ d;~-ul~- to the air flow. The strut on which the barrel is mount~ n~.~lly has a stre~mlined cross-section in fore and aft direction. Suitable strut l~;c~es~ has to be provided for de-icing heaters and also for carry~g ~e pl~Ul'~; signal cQndui or tubes.
It also has been lmown in the prior art to provide front and rear edges of air data sensor struts that are shaped in col~ d curves to ~n~ition from a folwa~dly-facing port to a side-mounting base for the air data sensor.
SU~M~RY OF l~F. INV~l~ON
The present invention relates to an air data sensor probe which can be for sensing pitot and/or static pl~s~ur~ that u~lizes a cylin-lric~l, forward-facing barrel having an open end for sensing pitot pleS~iUl'e. ~he barrel Wo 94/02858 2~ 37 Pcr/US93/06582 is ~up~l~d by a strut that curves rearwardly from the barrel and also laterally to a~Lch to a ...o...-~;ng base for ~~ E the air data sensor onto a ~ lg s~l~re The strut has div~ g front and rear edges that curve toward the ~o!~nl;ng base from the barrel. The strut is generally an ogival shape, with a s relatively rounded front edge which aids in C~e~ling ice, and thus reduces theamount of heat l~uucd during de-icing oper~tinn The barrel mounts to the strut with a support section that blends rapidly from cylin~ric~l to the ogival shape, using smooth surface conto~ to ~;ni...i~e drag. The air data sensing probe is small or compact and of low ~o weight when c~,np~ to other sensors in use, as well as being low in drag.
B~F nF-~cp~foN OF T~IF. nRAW~GS
Figure 1 is a top plan view of a s~rut - o~n~l air data sensor pr~be acco,~Llg to the present invention;
Figure 2 is a front elevational view of the device of Figure l;
Figure 3 is a ~ c lepr~ s~nl; ~;on of a top plan view of the device of Figure l;
Figure 4 is a s~ion~l view taken as on line 4--4 in Figure 3;
Figure S is a s~ion~l view ta~en as on line 5--5 in Figure 3;
Figure 6 is a ~ c-~ e view of the strut-mo~1nf~d air data sensor 20 probe made acco,ding to ~e present in-~lion.
D~TA~T Fn nF~ oN OF T~F p~2F.~-r l~RF.n F.MRODIM~
As shown in Figure 1, an air data sensing probe in~i~t~
genaally at 10 in Figure 1 i~l.d~s a crli.~ arrel por~on 12 that has an end opEni~ 14 facing toward the direction of air flow. The crlinti~ l barrel zs 12 is .no,~ d onto a strut se~ion 16, which in turn cu~es late~ally and r~dly from tbe ~ailing end of cylin~1n~l barrel 12, and late~ally from a central axis 18 of the cylin~lri~l barrel 12 toward a surface or sl~n 20 of an air -vehicle. The strut 16 has a mounting or plate base 22 that mounts to the air Wo 94/02858 ;2 14~37 PCI/US93/06582 vehicle in a convention~ cr. Generally, the outer side of the plate 22 is flush with the skin 20 so that drag is --;n;---;,~
As shown in Figure 2, the c~ d~ leading end opening 14 is across the entire intP.rn~ ~r of ~e barrel 12. The opening 14 fonns a 5 pitot pr~-llc sensing port facing in U~ ~lll direction to the air flow and is COl~t~ to sllit~hle tubing, not shown, within strut 16. The tubing has an end conn~ 13, which is joined to a suitable pl~'tUI~ sensor, not shown. The cylindrical barrel 12 is t~nCitinn~d to a g~onerally ogival cross-section shape of the strut 16 (as can be seen in Figures 4 and 5) in a short tr~ncition section 24 10 th~t smoothly blends the cylindrir~l shape of barrel 12 to the ogival cross-section of strut 16 in a ~ .. d;.l~ and ~.ill.oul having sharp or irregularedges. The cyli~ cAl ba~el 12 .-~ s a true ~lil-~.;~l sh~pe for a l length along its lo~tudin~ cis 18, which length is s~lbst~t;~lly equal to the tlict~nc~ b~.c~ thc placc of side surface 20 of the air vehicle and15 the barrel 12. The effec~ of the strut on air ~ in opc~g or port 14 is thus reduced to çnh~n~ re~iql ility of thc ~ gn~lc~
Tbe strut 16 itself has c4--~ curved front and rear (leading and tIailing) edges. A rounded (not sharp) leading edge 26.,~ ds ~b~ lly in a straight line ~djacrnt the air vehicle at a rcn~y inClin~d angle in~
zo at 28 ~ ,e to the air vehicle sur~cc 20. The leading edge 26 then curves at section 30 to ~ g~ lly joLn the outer surface of the ~lindlical barrel 12. The rear or traili;ng edge in~ t~d at 32 ~ ds at a gentle but dirf~ curve from the point where it joins the base 22 ~an the leading edge 26 folwa~ly and ouLw~u.]ly from the aircraft sldn 20 and base 22. The edges 32 and 26 converge 25 in direction toward the rear end of barrel 12, or, in other words, diverge indirection away from the barrel 12 bacl~ toward the base 22. A gentle, relativelylarge radius section 33 of the trailing edgè 32 blends into the outer surface ofthe cylindrical barrel 12.
WO 94~02858 PCI~/US93/06~82 ~a~7 As shown in Figure 2, the strut 16 also tapers in thicl~n~$5 along a central axis 35, which is shown generally in dotted lines at 34, so that the strut 16 is relatively thick or wide at its base portion 36 and reduces in size to a lateral ~;...~n~ on at 38 that is less than the 1i5~ r of the cylin~lric~l barrel s 12. Smoothly varying CG~ nd curved surfaces 39 are used for joining the strut 16 and the c~lind,i~al barrel 12. ~ef~ling to Figures 2, 3 and 6, the surfaces are srnoothly tapered to avoid irreg~ rities that will hlc~se drag or cause ~ul~ nl;zl air turb~ e On the upper surface of the strut 16, which is intli~t~ at 40, the tr~n~:ition section 24 has a bl~n~ surface 40A. The 10 blending surface 40A s~noothly enlarga in multiple directions from the surface 40, and enlarges to ~ .e c~l;nA~ l at about the line 46. This blending surfaoe also is d~igr~ to l~;n;~ f, drag wbile providing adequate ~U~ for the cylin~ fol w~ly di-~t~ barrel 12. A bottom surface 42 has a sirnilar enlarged surface bl~ ;~ to the cylin~lri~l barrel section 12, as shown in 42A
s in F;gure 6.
The sensor pr~>be 10 has heaters shown ~ ;~lly at 49 ln~t~ d in the strut 16 and also rnay have heaters in the barrel 12 for de-icing.
The heaters can be f~ '`'nGe heaters of conventional design. A suitable eonnr~Qr is-`shown at 50 in Figure 1 for el~ri~l c4/~nrcl;oll~ to the heaters 20 from the intc.iol of the air vehicle. The leading edge 26 of the strut 16 provides a r~undcd su~face tbat tends to shed ice. The rounded l~li~ edge 26 also provides an area for insertion of a r~ ~:c~n-~4 heater along and close to the edge 26 to increase the ~ s~ffi~p-ntly to melt or ie.llo~ the ice.
The ogival cross s~lion strut 16 is thin throughout its length to 2s reduce drag, and ~e quick ~nsition section 24 from the cylindrical or circular cross-section barrel 12 to a thin ogival strut section 16 is a smooth COlltOur~dsurface as well that tends to reduce weight, and decl~ drag. The transition section 24 extends in direction of axis 1~ prefe~bly in ~e range of one WO 94r02858 ~ 137 Pcr/US93/06582 ..ct~ r of the barrel 12. The tr~nCitio~ ~tio~C should be kept below two barrel ~i~m~ter in axial dir~tion.
The chord length to ll ;r~ s ratio, that is, the ~eral ~imPnciQn of the ogival cross s~tion indi~t~d at 26A in Figur~ 4 and 5 relative to ~e s chord ,easur~d from the leading to the trailing edges of the ogival strut and in~i~t~ at 26B, for eJtample, provides a st~ut that l~duces drag s~lb~ n and also ~ '5 the weight while providing adequate strength.
The ratio ~ the transverse ~ ;on 26A and the chordal on 26B may change s~l,sh r~ lly l~U'~UghoU~ the length of the strut 16.
0 In other words, ~lthough the strut 16 is ~inner where the chord length is shorter when "~u.~d normal to the cent~ is of the strut 16 the ~atio .~ g~s.
~lthough the ~ ~fid es 40A and 42A introduce a di~loc~tion in the flow, the blcn-l;ng area 24 ,~luccs this ~iclQ~ati~n~ The sulr~s of strut 16 areconve~ on the ~ .io- sides 40 and 42, as shown, and the walls of strut 16 are l~pt relatively thin. The ~du~ cross~ tion~l area of the strut 16 also enh~nC~s the anti-icing ~r~ Anc~. As previously stated, t_e effect of strut-induc~ ~ul~ enors on the .,.c~su~d pitot ~l~C opening 14 are also .eJu~. The ~I;nd. iC~l section of the barrel 12 provides for a large size pitot op~ning 14 relative to the ~ of the tube used.
- ~f~ling to Figure 3, a static p~, sensing port~~60 can be provided on the ~iyl;n~l~i~l barrel 12 at a desired loc~tiol- both as to annularposition around the barrel 12 and also lo~jtudin~l or a~ial positiol~ along the barrel 12. Usu~lly, the axis of the static sensing port is to the outer side of the probe and there Gm be two ports, one facing ~w~ly at about 60 from hGI ;7~ t 1 and the other dow--v/~dly also 60 from h.~ nl~l These a~es are shown at 60A in Figure 2. In such case, suitable plnmbin~ or tubing, not shown, is provided from the port 60 for carIying the static ~ u~ signals back through the strut 16 to the air vehicle.
.
2~4(~ ~37 Wo 94/02858 ~ PCI/US93/06582 The probe in one form, is very co~pact and light. Typically, for an e~mple of p~OI lions, the overall length of the base (A) as shown in Figure 1 may be from 3.5 to 4.5 inches: the length from the trailing out of the base to the tip of the barrel, (B) is 6.25 to 7.5 inches (less than 7.5 inches is p~f~.lod); the offset, (C) is 2.25 to 2.5 (less than 2.5 inches is pl~fel~d); and the barrel outside d;~ ter is typically .44 inches, to about .5 inches. In Figure 6, the barrel is shorter and the probe is about 6.5 inches in overall length.
The same general plopollions Gm be used in larger pitot-static ~ubes. For ey~n~rl~t where the overall leng~, ~B) may range up to 14 to 18 o inches with and the barrel length up to about 6 inches and the dia-- ~ about .75 to .9 inches.
~ltho1~h thc prcscnt invention has been dcs-- ;~d with r~f~ cc to ~l~f~l~ ;"..~c, . Jlh.~ slcilled in the art will l~C4~ , that ch~ngos may be made in form and detail without departing from the spirit and scope of 15 the in~ention.
The same general plopollions Gm be used in larger pitot-static ~ubes. For ey~n~rl~t where the overall leng~, ~B) may range up to 14 to 18 o inches with and the barrel length up to about 6 inches and the dia-- ~ about .75 to .9 inches.
~ltho1~h thc prcscnt invention has been dcs-- ;~d with r~f~ cc to ~l~f~l~ ;"..~c, . Jlh.~ slcilled in the art will l~C4~ , that ch~ngos may be made in form and detail without departing from the spirit and scope of 15 the in~ention.
Claims (10)
1. A pressure-sensing probe for mounting on an air vehicle a barrel having a generally cylindrical shape, a central axis centered on a diameter of the outer surface of the barrel, and a length along the central axis and a pressure sensing port;
a mounting base;
a strut extending between said mounting base and the barrel comprising curved leading and trailing edges that converge in direction from the mounting base toward the barrel and have a generally ogival cross-sectional shape, the strut extending to a position adjacent an end of the barrel; and a transition surface section interposed between the strut and the barrel that is smoothly countered to blend from the ogival cross-sectional shape of the strut to the cylindrical shape of the barrel.
a mounting base;
a strut extending between said mounting base and the barrel comprising curved leading and trailing edges that converge in direction from the mounting base toward the barrel and have a generally ogival cross-sectional shape, the strut extending to a position adjacent an end of the barrel; and a transition surface section interposed between the strut and the barrel that is smoothly countered to blend from the ogival cross-sectional shape of the strut to the cylindrical shape of the barrel.
2. The pressure sensing probe of claim 1 wherein the transition surface section has an axial dimension in direction along the central axis of the barrel that is not substantially greater than the diameter of the outer surface of the barrel.
3. The pressure sensing probe specified in claim 1 wherein the leading edge of the strut is rounded in cross section when compared to the trailing edge of the strut, which forms a sharp edge in cross section.
4. The pressure sensing probe as specified in claim 1 wherein the barrel has a pitot pressure sensing opening at a leading end of the barrel and facing upstream relative to an air flow, the opening having a diameter substantially equal to an inner diameter of the barrel.
5. The pressure sensing probe of claim 1 wherein the pressure sensing port comprises an opening in a leading end of the barrel relative to movement of fluid past the barrel.
6. The pressure sensing probe of claim 5 and a separate static pressure sensing port on the barrel spaced from the leading end.
7. The pressure sensing probe of claim 5 wherein the barrel comprises a tube having an interior bore extending along the central axis and the bore opening to the leading end to form the pressure sensing port.
8. The pressure sensing probe of claim 1 wherein the barrel comprises a straight tube having a substantially uniform outer surface diameter throughout its length and having a substantially uniform diameter bore extendingfrom a leading end of the barrel to position adjacent to the strut, the leading end of the bore forming the pressure sensing port.
9. The pressure extending probe of claim 1 and heater means on the probe for eliminating ice accumulation.
10. The pressure sensing probe of claim 1 wherein the transition section has an axial length of less than 2 times the diameter of the barrel.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US07/916,498 | 1992-07-20 | ||
| US07/916,498 US5331849A (en) | 1992-07-20 | 1992-07-20 | Aerodynamically shaped probe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2140137A1 true CA2140137A1 (en) | 1994-02-03 |
Family
ID=25437374
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002140137A Abandoned CA2140137A1 (en) | 1992-07-20 | 1993-07-13 | Aerodynamically shaped probe |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US5331849A (en) |
| EP (1) | EP0651885B1 (en) |
| JP (1) | JPH08501623A (en) |
| CA (1) | CA2140137A1 (en) |
| DE (1) | DE69326153T2 (en) |
| WO (1) | WO1994002858A1 (en) |
Families Citing this family (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5466067A (en) * | 1993-09-17 | 1995-11-14 | The B. F. Goodrich Company | Multifunctional air data sensing probes |
| US5601254A (en) * | 1994-10-28 | 1997-02-11 | Rosemount Aerospace Inc. | Single sided backbone strut for air data sensor |
| US5616861A (en) * | 1995-06-07 | 1997-04-01 | Rosemount Aerospace Inc. | Three pressure pseudo -Δ-P sensor for use with three pressure air data probe |
| US5653538A (en) * | 1995-06-07 | 1997-08-05 | Rosemount Aerospace Inc. | Total temperature probe |
| US6271769B1 (en) | 1997-12-02 | 2001-08-07 | Proprietary Software Systems, Inc. | Apparatus and method for measuring and displaying angular deviations from angle of zero lift for air vehicles |
| RU2152042C1 (en) | 1998-05-26 | 2000-06-27 | Центральный аэрогидродинамический институт им. проф. Н.Е. Жуковского | High-pressure tube ( variants ) |
| US6430996B1 (en) | 1999-11-09 | 2002-08-13 | Mark Anderson | Probe and integrated ice detection and air data system |
| FR2808874B1 (en) * | 2000-05-15 | 2002-07-26 | Auxitrol Sa | SENSOR FOR MEASUREMENT OF PHYSICAL PARAMETERS ON A FLUID FLOW AND IN PARTICULAR AIR TEMPERATURE SENSOR |
| JP3749135B2 (en) * | 2001-03-13 | 2006-02-22 | 横河電子機器株式会社 | Temperature measuring device |
| US6892584B2 (en) * | 2002-11-19 | 2005-05-17 | Rosemount Aerospace Inc. | Fabricated pitot probe assembly |
| FR2904874B1 (en) * | 2006-08-09 | 2009-04-03 | Eurocopter France | METHOD AND DEVICE FOR MEASURING THE SPEED OF AN AIRCRAFT, IN PARTICULAR A LOW-SPEED GIRAVION |
| US8100582B1 (en) * | 2007-12-13 | 2012-01-24 | Powell Bradley J | Temperature probe |
| US8813577B1 (en) * | 2011-11-22 | 2014-08-26 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Self-contained compressed-flow generation device for use in making differential measurements |
| US10585109B2 (en) | 2014-06-02 | 2020-03-10 | University Of Kansas | Systems, methods, and devices for fluid data sensing |
| US9541429B2 (en) | 2014-06-02 | 2017-01-10 | University Of Kansas | Systems, methods, and devices for fluid data sensing |
| US9909905B2 (en) * | 2015-10-15 | 2018-03-06 | Honeywell International Inc. | Multi-part air data probe assembly to facilitate rapid replacement |
| CA2966743C (en) * | 2016-07-15 | 2023-06-27 | Rosemount Aerospace Inc. | Air data probe with turbulence-producing geometry |
| US11549914B2 (en) * | 2020-12-21 | 2023-01-10 | Hamilton Sundstrand Corporation | Surface acoustic wave sensors for air data probes |
Family Cites Families (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2204367A (en) * | 1938-05-03 | 1940-06-11 | Square D Co | Trapped self-draining pitot-static tube |
| GB857427A (en) * | 1958-04-03 | 1960-12-29 | Avimo Ltd | Improvements in and relating to pitot tube devices |
| US3030807A (en) * | 1959-11-19 | 1962-04-24 | Aero Res Instr Co Inc | Heated pitot tube assembly |
| US3163040A (en) * | 1962-01-04 | 1964-12-29 | Rosemount Eng Co Ltd | De-iced pitot static tube |
| US3318146A (en) * | 1966-02-14 | 1967-05-09 | Rosemount Eng Co Ltd | Pressure sensing instrument for aircraft |
| US3482445A (en) * | 1968-04-25 | 1969-12-09 | Rosemount Eng Co Ltd | Strut mounted dual static tube |
| US4096744A (en) * | 1975-09-05 | 1978-06-27 | Rosemount Inc. | Pressure sensor for determining airspeed, altitude and angle of attack |
| US4275603A (en) * | 1979-11-23 | 1981-06-30 | The Boeing Company | Indirectly heated aircraft probes and masts |
| US4378696A (en) * | 1981-02-23 | 1983-04-05 | Rosemount Inc. | Pressure sensor for determining airspeed altitude and angle of attack |
| US4378697A (en) * | 1981-07-06 | 1983-04-05 | Rosemount Inc. | Strut mounted multiple static tube |
| US4615213A (en) * | 1983-12-22 | 1986-10-07 | Rosemount Inc. | Pressure sensing instrument for aircraft |
| US4730487A (en) * | 1985-06-04 | 1988-03-15 | Rosemount Inc. | Family of aerodynamically compensated multiple static pressure tubes |
| US4645517A (en) * | 1985-09-20 | 1987-02-24 | Rosemount Inc. | Drain manifold for air data sensor |
| US4718273A (en) * | 1985-12-31 | 1988-01-12 | The Garrett Corporation | Combination alpha, static and total pressure probe |
| US4836019A (en) * | 1987-08-27 | 1989-06-06 | Rosemount Inc. | Compact air data sensor |
| US5025661A (en) * | 1989-12-11 | 1991-06-25 | Allied-Signal Inc. | Combination air data probe |
| DE69127466T2 (en) * | 1991-03-22 | 1998-03-19 | Goodrich Co B F | INTERRUPTED CURVED SENSOR |
-
1992
- 1992-07-20 US US07/916,498 patent/US5331849A/en not_active Expired - Lifetime
-
1993
- 1993-07-13 EP EP93917151A patent/EP0651885B1/en not_active Expired - Lifetime
- 1993-07-13 WO PCT/US1993/006582 patent/WO1994002858A1/en active IP Right Grant
- 1993-07-13 DE DE69326153T patent/DE69326153T2/en not_active Expired - Lifetime
- 1993-07-13 CA CA002140137A patent/CA2140137A1/en not_active Abandoned
- 1993-07-13 JP JP6504530A patent/JPH08501623A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| DE69326153T2 (en) | 2000-03-16 |
| EP0651885A1 (en) | 1995-05-10 |
| JPH08501623A (en) | 1996-02-20 |
| EP0651885B1 (en) | 1999-08-25 |
| US5331849A (en) | 1994-07-26 |
| WO1994002858A1 (en) | 1994-02-03 |
| DE69326153D1 (en) | 1999-09-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FZDE | Discontinued |