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    • 5. 发明专利
    • AIR INTRODUCING TYPE ROCKET
    • JPH03220096A
    • 1991-09-27
    • JP1703490
    • 1990-01-25
    • NISSAN MOTOR
    • YAMAMOTO YOICHIONOSHIMA NOBORU
    • B64G1/00
    • PURPOSE:To permit the spin of a rocket in flying and stabilize the flying in the direction of the axis of the machine by arranging an outer cylinder forming a secondary combustion chamber on the periphery of an injection nozzle and installing a spinning means for spinning a rocket in the secondary combustion chamber. CONSTITUTION:When the propellant in a primary combustion chamber 19 is ignited, the combustion gas is jetted into a secondary combustion chamber through an injection nozzle 12 from the primary combustion chamber. At the same time, air is introduced into the secondary combustion chamber from the front edge part of an outer cylinder 13, and the air and the combustion gas are violently mixed and combusted in the secondary combustion chamber, and jetted from the secondary combustion chamber, and a prescribed propulsion force is obtained. Since, in this case, a rocket is spun by the injection nozzle 12 installed in the secondary combustion chamber, the flying in the direction of axis of the machine is stabilized, and the air and the combustion gas flow in spiral form in the outer cylinder 13, and the mixing efficiency in the secondary combustion chamber 20 is improved. Accordingly, even if the total length of the secondary combustion chamber, i.e., the total length of the outer cylinder is shortened, the mixing and combustion can be carried out satisfactorily.
    • 9. 发明专利
    • LOAD-CARRYING PLATFORM STRUCTURE ON TRUCK
    • JPH0427678A
    • 1992-01-30
    • JP13035290
    • 1990-05-22
    • NISSAN MOTOR
    • YAMAMOTO YOICHI
    • B62D33/03
    • PURPOSE:To load a long cargo by lifting the long cargo along a vertical rail without removing a rear gate and horizontally containing it on a protrusion part formed to the upper part of the inner side of the rearmost part of a side panel when the long cargo longer than a load-carrying platform is loaded. CONSTITUTION:A vertical rail 20 is installed on an inner surface 24a of the rearmost part of a side panel 24 of a cargo box and formed to a rotation fulcrum 23a position on the side panel side in a manner that a hinge 22 position being the rotation fulcrum of a rear gate 21 of a normal truck is located to the lower end of the rear gate. A horizontal rail 25 is formed from the upper end of the vertical rail 20 along the upper edge of the side panel 24 and a protrusion part 28 for placing a rear gate 21 is formed below a horizontal rail 25. Rotary fulcrums 23b on the rear gate side of a link arm 23 are positioned in the vicinity of the upper ends of the side parts on both sides of the rear gate 21. A rotary fulcrum 23a on the side panel side is slidably located to the horizontal rail 25 and an assist spring 30 energizing toward the front of a chassis is connected to the rotary fulcrum 23a on the side panel side.
    • 10. 发明专利
    • ROCKET MOTOR
    • JPH03130564A
    • 1991-06-04
    • JP26760289
    • 1989-10-12
    • NISSAN MOTOR
    • YAMAMOTO YOICHIONOSHIMA NOBORU
    • F02K9/30
    • PURPOSE:To prevent generation of erosive burning by arranging an injection nozzle, which injects combustion gas generated in a combustion chamber toward the rear, in the intermediate part periphery of a rocket motor main unit in a position where a generated amount of combustion gas is almost equal in both front and rear side combustion parts. CONSTITUTION:A rocket main unit 1 is formed of both front and rear cylinder units 2, 3 and an annular nozzle mounting member 4 for connecting these cylinder units. While the lower from the intermediate part of the rocket main unit 1, that is, the rear from a rear end part of the front part cylinder unit 2 is floating-fitted into an outer cylinder 10. Further a secondary combustion chamber 13 is formed between the rocket main unit 1 and the outer cylinder 10. Here in the periphery of the intermediate part, which is in the point end part of the secondary combustion chamber 13, in the rocket main unit 1, a plurality of injection nozzles 14 for injecting combustible gas are arranged in the peripheral direction with an equal pitch. Each injection nozzle 14 is arranged in a position where combustible gas, generated in a plurality of combustion chambers 7, 8 set so as to almost equalize a generated combustible gas amount, is simultaneously jetted.