WITHDRAWAL OF CARRIER ROCKET STAGE SEPARATED PART FROM PAYLOAD ORBIT AND DEVICE TO THIS END Russian patent published in 2014 - IPC F02K9/42 B64G1/26 

FIELD: engines and pumps.

SUBSTANCE: invention relates to liquid-propellant rockets, accelerating units and can be used at starting the engines when liquid-propellant store residues do not exceed 3% of initial value. Proposed method consists in gasification of liquid residues of unusable fuel reserve in oxidiser and combustible tanks, generation of braking pulse by their combustion in combustion chamber of gas rocker engine and high-rate blowdown of combustion products into space. In compliance with this invention, solid-propellant gas generating compounds (SPGGC) are used for gasification of unusable rocket propellant reserve. SPGGC is fed to oxidiser tank with excess oxygen while SPGGC with limited content of oxygen is fed to fuel tank. Note here that chemical composition and mount of SPGGC at minimum possible residues of unusable rocket propellant components are defined proceeding from preset characteristic speed: $$\Delta V_{\Sigma }^{preset}=\Delta V_{res}^{SPGGC}+\Delta V_{SPGGC}^{SPGGC},$$ where $$\Delta V_{\Sigma }^{preset}$$ is characteristic speed, $$\Delta V_{res}^{SPGGC}$$ is pulse developed owing to minimum unusable residues of rocket propellant in both tanks required for their oxidation, $$\Delta V_{SPGGC}^{SPGGC}$$ is the pulse developed only by combustion of SPGGC gases in gas rocket engine. Proposed device comprises engine with oxidiser and fuel tanks, tank supercharge system, has rocket engine with power supply system and rocket propellant component residues gasification system. Note here that engine plant is equipped with solid-propellant gas generators with their outlets connected with gas feed devices. Said gas generators are equipped with pyro membranes fitted in fuel tanks with residues of liquid rocket fuel.

EFFECT: higher efficiency.

3 cl, 1 dwg, 1 tbl