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rocket propellant
The detection of defects and the characterization of solid rocket propellant were thus possible.
      
We have considered the electrodynamic effects on small Al2O3 spherules dumped into the Earth's magnetosphere in large quantities during solid rocket propellant burns.
      
TG studies of a composite solid rocket propellant based on HTPB-binder
      
The reasons for substantially nonstationary modes of operation of this system are considered, and a simplified model that approximates the phenomena of nonstationary combustion of a solid rocket propellant is proposed.
      
The paper presents estimates of the dynamic characteristics of unsteady combustion of a solid rocket propellant in a combustion chamber with in pressure is varied automatically by a specified program.
      
Examples are a marine coating on a ship, the protective coating on the liner of an acid containing tank, a rocket propellant, an adhesive in a bond joint, or the polymer in a composite structure.
      
A two-dimensional model of the transversal cross section of a bonded rocket propellant grain was subjected to uniform and steady thermal loading and, alternatively, to mechanically applied uniform radial displacements on the outer boundary.
      
Experimental means of analyzing stresses and strains in rocket propellant grains
      
By contrast, ballistic missiles are powered by rocket propellant, which also controls their trajectory.
      
No such solutions are available for impellers such as are commonly used in high-performance pumpsfor rocket propellant applications.
      
One can see that there are both positive and negative aggregates formed in combustion of solid rocket propellant.
      
Solid rocket propellant is a composite of aluminum particles in an oxidizing matrix.
      
Traction tests were performed on RPI, a common kerosene based rocket propellant.
      
Traction tests were performed on R_I, a common kerosene based rocket propellant.
      
These exploration activities lead to the establishment of a lunar camp and base which produce oxygen and possibly hydrogen for rocket propellant.
      
The objective of this program was to compare reclaimed AP with virgin AP in a baseline rocket propellant formulation.
      
The properties given in the spreadsheet are for a typical composite rocket propellant with a central perforation contained in a graphite/epoxy case.
      
The objective of this paper is to study mechanism of alumina aggregate formation under combustion of solid rocket propellant.
      
The silicon or light metals may also be used as fuel for a fully lunar-derived rocket propellant.
      
 

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