Controllable thrust multi-pulse solid rocket engine
A solid rocket and motor technology, applied in rocket motor devices, machines/engines, mechanical equipment, etc., can solve the problems of difficulty in determining the electric power of electronically controlled solid propellants, and difficulty in guaranteeing
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Embodiment 1
[0134] see Figure 3-5 , a multi-pulse solid rocket motor with controllable thrust, is characterized in that:
[0135] It mainly includes combustion chamber A11, control system 21 and power supply 31.
[0136] The combustion chamber A11 includes an electronically controlled solid propellant A101, an electrode AI102, an electrode AII103, an insulating layer A104, a combustion chamber casing A105, a pressure sensor A106, and a nozzle A107.
[0137] A layer of insulating paint is coated on the inner wall of the combustion chamber housing A105. One end of the combustion chamber casing A105 is a nozzle A107, and the other end has a through hole for the electrode AII103 to penetrate.
[0138] The interior of the combustion chamber housing A105 is filled with electronically controlled solid propellant A101. One end of the electronically controlled solid propellant A101 faces the nozzle A107. The electronically controlled solid propellant A101 is covered with conductive material. ...
Embodiment 2
[0156] see Figure 6-8 , a multi-pulse solid rocket motor with controllable thrust, characterized in that:
[0157] It mainly includes combustion chamber B11, control system 21 and power supply 31.
[0158] The combustion chamber B11 includes an electronically controlled solid propellant B101, an electrode BI102, an electrode BII103, an insulating layer B104, a combustion chamber casing B105, a pressure sensor B106, and a nozzle B107.
[0159] A layer of insulating paint is coated on the inner wall of the combustion chamber housing B105. One end of the combustion chamber housing B105 is a nozzle B107, and the other end has a through slot for the electrode BII103 to penetrate.
[0160] The combustion chamber housing B105 is filled with electronically controlled solid propellant B101. One end of the electronically controlled solid propellant B101 faces the nozzle B107.
[0161] One side of the electronically controlled solid propellant B101 is in contact with the flat electr...
Embodiment 3
[0179] see Figures 9 to 11 , a multi-pulse solid rocket motor with controllable thrust, is characterized in that:
[0180] It mainly includes combustion chamber C11, control system 21 and power supply 31.
[0181] The combustion chamber C11 includes an electronically controlled solid propellant C101, an electrode CI102, an electrode CII103, an insulating support rod C104, a combustion chamber casing C105, a pressure sensor C106, and a nozzle C107.
[0182] A layer of insulating paint is coated on the inner wall of the combustion chamber housing C105. One end of the combustion chamber casing C105 is connected to the nozzle C107, and the other end has a through hole for the telescopic rod of the transmission device 200 to penetrate.
[0183] The interior of the combustion chamber casing C105 is filled with electronically controlled solid propellant C101. One end of the electronically controlled solid propellant C101 faces the nozzle C107. The electronically controlled solid...
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