http://rdf.ncbi.nlm.nih.gov/pubchem/patent/GB-656331-A
Outgoing Links
| Predicate | Object |
|---|---|
| assignee | http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_a4d624ef62ec5b6e7ba4de7df5392257 http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_1ea4b1e9f213278b756600c656e94916 http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_7b8509c780bd1bfc6c0ab3819cebdd47 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K9-68 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K9-68 |
| filingDate | 1949-01-03-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationDate | 1951-08-22-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | GB-656331-A |
| titleOfInvention | Improvements in or relating to rocket type propulsion apparatus |
| abstract | 656,331. Jet propulsion plant. DE HAVIL LAND ENGINE CO., Ltd., HALFORD, F. B., and CLEAVER, A. V. Jan. 3, 1949, No. 74. [Class 110(iii)] A rocket propulsion unit for ,assisting the take-off of an aircraft comprises a main propellant reservoir 11, Fig. 2, a reaction chamber 10 extending rearwardly from this reservoir and terminating in a convergentdivergent nozzle 25, a second propellor reservoir 12 formed as an annular chamber around the nozzle and one or more compressed air or gas containers 13 arranged around the reaction chamber 10 between the two reservoirs. The main propellant may be hydrogen peroxide and the second propellant may be a dissociation catalyst e.g. sodium or calcium permanganate. These liquids are injected into the reaction chamber 10 by compressed air from the bottles 13. The compressed air passes first through an automatic reducing valve 14, Fig. 1, and then through a shut-off valve 15 to a check thrust valve 16. After leaving the valve 16 it passes to a starting valve 17 which when opened allows the air to open a catalyst air distributer valve 18. The valve 18 then allows compressed air to flow through a pipe 19 into the reservoir 12. A part of the latter air opens the hydrogen peroxide air distributer valve 21 and allows a further supply of compressed air to flow through a pipe 22 into the reservoir 11. The operation and construction of the valves may be as described in Specifications 656,332, 656,333, 656,334 and 656,335. The bottles 13 are supported at their forward ends by brackets 26 attached to the reservoir 11 and at the rearward ends by an annular manifold 27 secured to a web 28 supported on the reaction chamber 10. The propulsion unit is mounted on the aircraft by a boss 29 at the forward end of the reservoir 11 and two bosses 30 on opposite sides of its rear end. For handling the unit when it is removed from the aircraft slinging points 31 and 32 are provided. The centre of gravity or the unit is preferably so arranged that, when full, it lies within the triangle formed by the points 29, 30 and when empty, between the points 31, 32. |
| priorityDate | 1949-01-03-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 18.