DETAILED ACTION
Notice of Pre-AIA or AIA Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
Claim Rejections - 35 USC § 102
The following is a quotation of the appropriate paragraphs of 35 U.S.C. 102 that form the basis for the rejections under this section made in this Office action:
A person shall be entitled to a patent unless –
(a)(1) the claimed invention was patented, described in a printed publication, or in public use, on sale, or otherwise available to the public before the effective filing date of the claimed invention.
Claims 1-15 are rejected under 35 U.S.C. 102(a)(1) as being anticipated by Aubonnet (US 2009/0126737 A1). Aubonnet discloses:
1. An aircraft oxygen supply system, comprising:
at least one oxygen mask (610)
an oxygen supply (600), and
a pressure reducer (10), interposed between the oxygen supply and the at least one oxygen mask, wherein the pressure reducer comprises:
a housing (11,12);
a piston (20), which is axially movable within the housing;
a high pressure inlet (115), which is provided on a high pressure side (11) of the housing and which is coupled to the oxygen supply;
a pressure reducing gas flow path (18), connecting the high pressure inlet (115) and an axial gas flow channel (207) within the piston;
a reduced pressure outlet (125), which is provided on a reduced pressure side (12) of the housing and to which the axial gas flow channel opens; and
a pressure control chamber (19), which extends radially from the reduced pressure outlet and which is interposed between the housing and a reduced pressure end face of the piston.
2. The aircraft oxygen supply system according to The aircraft oxygen supply system according to
wherein the housing of the pressure reducer comprises a piston stop surface (116) for the reduced pressure end face of the piston, and
wherein the pressure control chamber of the pressure reducer comprises a recess (scooped out area just behind 116) in the housing with respect to the piston stop surface and/or wherein the pressure control chamber of the pressure reducer comprises a recess in the reduced pressure end face of the piston.
3. The aircraft oxygen supply system according to claim 1, wherein the piston of the pressure reducer comprises a cavity (207) in the reduced pressure end face, and wherein the axial gas flow channel opens (at 125) into the cavity.
4. The aircraft oxygen supply system according to claim 3, wherein an end portion of the axial gas flow channel is formed by a collar (21) in the cavity.
5. The aircraft oxygen supply system according to claim 1, wherein at least one of the high pressure inlet, the axial gas flow channel, the pressure control chamber, and the reduced pressure outlet is cylindrical (each appear cylindrical).
6. The aircraft oxygen supply system according to claim 1, wherein the axial gas flow channel (207) has a first cross-sectional extension, wherein the pressure control chamber (19) has a second cross-sectional extension, and wherein the reduced pressure outlet (125) has a third cross-sectional extension (compare sizes in Fig. 4, 207 is at least smaller at 205 compared to 125).
7. The aircraft oxygen supply system according to claim 6, wherein the third cross-sectional extension is between 2 times and 10 times, as large as the first cross-sectional extension (since it reaches all the way out to 111).
8. The aircraft oxygen supply system according to claim 6, wherein the second cross-sectional extension is between 2 times and 8 times as large as the third cross-sectional extension (since it extends all the way out to housing 12).
9. The aircraft oxygen supply system according to claim 1, wherein a radial extension of the pressure control chamber is between 30 times and 50 times as large as an axial extension of the pressure control chamber (since it extends all the way out to housing 12).
10. The aircraft oxygen supply system according to claim 1, wherein the reduced pressure outlet is tapered (see curvature of 125 when it reaches 12) with respect to the pressure control chamber.
11. The aircraft oxygen supply system according to claim 1, wherein the at least one oxygen mask is a plurality of oxygen masks (three masks in Fig. 1).
12. The aircraft oxygen supply system according to claim 1, further comprising a controller (“818 is controlled by a pilot valve 822.”; Paragraph [0015]) configured to provide pulses of reduced pressure oxygen from the reduced pressure outlet of the pressure reducer to the at least one oxygen mask.
13. The aircraft oxygen supply system according to claim 1, wherein the oxygen supply comprises an oxygen bottle, in particular an oxygen bottle filled with compressed oxygen, or an oxygen generator or a connection to a central oxygen source (600).
14. The aircraft oxygen supply system according to The aircraft oxygen supply system according to
wherein the aircraft oxygen supply system is an aircraft emergency oxygen supply system (“mask in case of an emergency”; Paragraph [0002]); or wherein the aircraft oxygen supply system is arranged in a passenger service unit, in particular arranged in an overhead passenger service unit.
15. An aircraft (“"jumbo" or "super-jumbo" aircraft of very large capacity”; Paragraph 0002] including:
at least one aircraft oxygen supply system as recited in claim 1.
Conclusion
The prior art made of record and not relied upon is considered pertinent to applicant's disclosure. Each of the other prior art show pressure reducers with plungers and a high and low pressure side.
Any inquiry concerning this communication or earlier communications from the examiner should be directed to BRIAN M O'HARA whose telephone number is (571)270-5224. The examiner can normally be reached Monday - Friday, 9AM - 5PM eastern.
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If attempts to reach the examiner by telephone are unsuccessful, the examiner’s supervisor, Joshua Huson can be reached at 571-270-5301. The fax phone number for the organization where this application or proceeding is assigned is 571-273-8300.
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/BRIAN M O'HARA/Primary Examiner, Art Unit 3642