Development of a Cockpit Architecture for the Dream Chaser Orbital Vehicle

2012 ◽  
Author(s):  
L. Zea ◽  
S. Over ◽  
D. Klaus ◽  
J. Tanner ◽  
K. Stroud
Keyword(s):  
Orbital Vehicle

Structural dynamic analysis of the X34 orbital vehicle engine

1996 ◽  
Author(s):  
Andrew Brown ◽  
Donald Harris ◽  
Samuel Fowler ◽  
Katherine Mims
Keyword(s):  
Dynamic Analysis ◽  
Structural Dynamic ◽  
Vehicle Engine ◽  
Orbital Vehicle

MOMENTAL METHOD FOR CALCULATING FORCES IN CYLINDRICAL SHELLS OF ORBITAL FACILITIES

2020 ◽  
Author(s):  
Lev Gorshkov ◽  
Aleksey Sof'in ◽  
Igor' Urtmincev ◽  
Aleksandr Levandovich
Keyword(s):  
Bending Moment ◽  
Middle Surface ◽  
Inertial Forces ◽  
Mathematical Algorithm ◽  
Normal Forces ◽  
Longitudinal Plane ◽  
Radial Displacements ◽  
The Moment ◽  
Maneuvering Spacecraft ◽  
Orbital Vehicle

The article is devoted to the torque method, according to the principles of which it is possible to determine the loads arising in the thin-walled shell of the hulls of orbital vehicles from the action of the internal pressure uniformly distributed over the area, normally oriented to the middle surface of the shell. In this case, the load on the shell consists of normal forces (longitudinal and circumferential), a transverse force that causes radial displacements in the shell, and a bending moment in the longitudinal plane of the object. The specified bending moment can occur during the manifestation of inertial forces (for example, the Coriolis force) during the transition of the orbital vehicle in height from one orbit to another in vertical directions normal to the orbit (rotational movements); the same rotary movements can cause inertial forces to appear when maneuvering spacecraft and rocket units at the same height (in conventionally horizontal directions). To determine the above loads and radial displacements of the shell, a mathematical algorithm is proposed based on the principles of the moment calculation method according to the scheme of an infinitely long shell, which is typical for orbital vehicle housings.

Specifics of designing trajectories of perspective spacecraft for Venus exploration

2021 ◽  
Author(s):  
A.V. Simonov ◽  
S.D. Kovaleva ◽  
E.S. Gordienko ◽  
V.G. Paul ◽  
A.V. Kosenkova
Keyword(s):  
High Temperature ◽  
Data Transfer ◽  
Elliptical Orbit ◽  
Lower Atmosphere ◽  
Mission Profile ◽  
Orbital Vehicle ◽  
Profile Development

The paper describes the mission profile of the perspective Venus exploration project spacecraft with launches planned for 2027−2031. The main aspects of selecting the optimal launch dates are considered. The sequences of an orbiter injection to a highly elliptical orbit and a lander delivery to the surface of Venus are described. The rationale for the operating orbit as well as for the injection sequence that will enable Venus-to-Earth data transfer are provided. The lifespan of the lander, including its parachute descent, is limited by the high temperature of the lower atmosphere close to the surface (up to 460 degrees Celsius) and is expected to be no more than three hours. Therefore, a key feature of the mission profile development is designing the sequence of the orbital vehicle maneuvers, which ensures robust communication with the lander during this time within a range of 40 thousand kilometers.

Dynamic Derivative Computation of a Sub-orbital Vehicle

2013 ◽  
Author(s):  
C. Marongiu ◽  
Frank Tarfeld ◽  
Harry Adirim ◽  
Norbert A. Pilz
Keyword(s):  
Orbital Vehicle
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