Patent US3888079A successfully refreshed from Google Patents.
US3888079A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Solid propellant rocket motor
Assignee: Dynamit Nobel AG
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Filing: 1973-03-26
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Granted: 1975-06-10
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Expires: 1993-03-26
Abstract
Abstract A rocket motor having at least two coaxial combustion chambers, one arranged behind the other and each containing a solid propellant charge. A partition is positioned between the first and second chamber and between each successively sets or pairs of chambers. This partition has closure means for preventing ignition of the second charge during ignition of the first and for allowing through flow due to excess pressure generated by ignition of the second propellant charge.
Inventors
- 👤 Walter Helmut Diesinger
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 05:00
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/74; F02K9/76; F02K9/763; F02K9/08; F02K9/28; F02K9/32; F02K9/38; F02K9/97; F02K9/978; Y; Y10; Y10T; Y10T137/00; Y10T137/1624; Y10T137/1632; Y10T137/1789
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
151 words
In a solid propellant rocket motor with two or more coaxially arranged combustion chambers containing propellant charges of the same or of a different efficiency arranged in series one behind the other, which chambers cooperate with a common nozzle, are each equipped with one igniting device activatable in a predetermined time interval, and are secured with respect to each other against unintentional burning, the improvement which comprises partition means for separating the propellant charges from each other including closure means that open up, at least partially, to provide a throughflow cross-section due to the excess pressure caused by ignition of the subsequent propellent charge, said partition means including a perforated plate and said closure means including holes in said plate which are sealed by plugs, and means arranged on the side of the perforated plate opposite from said nozzle and attached to said plugs for securing said plugs to said plate.
Claim 2
Dependent Claim
151 words
In a solid propellant rocket motor with two or more coaxially arranged combustion chambers containing propellant charges of the same or of a different efficiency arranged in series one behind the other, which chambers cooperate with a common nozzle, are each equipped with one igniting device activatable in a predetermined time interval, and are secured with respect to each other against unintentional burning, the improvement which comprises partition means for separating the propellant charges from each other including closure means that open up, at least partially, to provide a throughflow cross-section due to the excess pressure caused by ignition of the subsequent propellent charge, said partition means including a perforated plate and said closure means including holes in said plate which are sealed by plugs, and means arranged on the side of the perforated plate opposite from said nozzle and attached to said plugs for securing said plugs to said plate.
Claim 3
Dependent Claim
38 words
The solid propellant rocket motor of claim 1, in which the sum of the cross-sectional area of all the holes in the perforated plate is larger than the narrowest cross-sectional area of the nozzle of the rocket motor.
Claim 4
Dependent Claim
19 words
The solid propellant rocket motor of claim 1, in which the plugs are made of a soft resilient material.
Claim 5
Dependent Claim
29 words
The solid propellant rocket motor of claim 3, in which the plugs and/or the entire partition are protected by a radiation-reflecting and/or heat-absorbing layer positioned on the nozzle side.
Claim 6
Dependent Claim
28 words
A solid propellant rocket motor of claim 1, in which the means for securing said plugs include a plurality of flat springs, one for each of said plugs.
Claim 7
Dependent Claim
40 words
The solid propellant rocket motor of claim 1, in which the the means for securing said plugs include a foil arranged on the side of the perforated plate opposite from said nozzle, said foil being secured to said perforated plate.
Claim 8
Dependent Claim
18 words
The solid propellant rocket motor of claim 1 in which the plugs are each of a conical configuration.
Claim 9
Dependent Claim
58 words
The solid propellant rocket motor of claim 1 in which the holes in the perforated plate are arranged in a stellate pattern with one hole being in the center of the plate and the others being spaced therefrom, the distance from the other holes to the central hole being smaller than the spacing between said other adjacent holes.
Claim 10
Dependent Claim
22 words
The solid propellant rocket motor of claim 1 in which the perforated plate is thinner in the center than along it periphery.
Claim 11
Dependent Claim
32 words
The solid propellant rocket motor of claim 1 in which one or more of the propellant charges on the nose side contain ejectable substances which practically do not serve for propulsion purposes.
Claim 12
Dependent Claim
26 words
The solid propellant rocket motor of claim 1 in which a braking device can be actuateD by one or more propellant charges on the nose side.
References Cited (Backward Citations)
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-06-09 | 1978-12-09 | 1979-06-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-06-09 | 1982-12-09 | 1983-06-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-06-09 | 1986-12-09 | 1987-06-10 | $7700.00 | Window Closed / Lapsed |