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Rendezvous in orbit fuel consumption of pulses

(Vo + Avo) for any constant ≠ 0, when,, = (1) 0, can be obtained to open the old four identity: Text will be in cyberspace empty fuel consumption of Impulse Orbit 53 = A0 10 【】 Port + (1 a cosg.3E) where A :-------~( r, a, {}) a √ Pi (n) to Y0 ten voAro, the imposition of the first velocity pulse, the velocity vector and position vector parallel to the ellipse degenerates to a straight line. In fact such a campaign could not have happened, that when g ≠ O, regardless of how much the speed increment and the length of time (tl-to), can not achieve through the double-pulse orbit r = (1 口) 0 transfer. Under normal circumstances,, = 0P (r is any scalar, p is any vector perpendicular to the 0), then the situation is more complicated. According to the equations of motion, given arbitrary time (r-t0)> 0, can achieve orbit transfer. However,[link widoczny dla zalogowanych], due to the Earth's block,[link widoczny dla zalogowanych], and in some [f, p, (f, a t0)] defined area, orbit transfer impossible. Based on the above (1), (2) In both cases, we can see that the analysis of CW two-pulse orbit and its neighboring points are not up to the high energy region does exist, not because of linearization and approximation result. Of course, the linearization and approximation will lead to the calculation of singular points in and around the data and the actual value of a large deviation, but the reflection of the law is correct. On the physical meaning is not up to point to Figure 3 as an example to illustrate. When r = (1 +) r0, the possible double-pulse orbit by the spacecraft from the (0, vo) to reach (r, v1). Put in place because no matter how much r0 0, after a cycle of operation,[link widoczny dla zalogowanych], the spacecraft must return, o at, but impossible to reach, unless applied at △, the (0 ten o) and o total, linear movement to reach This fuel consumption is quite amazing. Obviously, rr of the neighborhood is the high energy region. In short, to make the spacecraft from (t0, 0,0) to reach (tr,, r, vf), △ is applied after the transfer orbit must pass, o and,[link widoczny dla zalogowanych],,, and the focus of the ellipse is the center of the earth arc the transfer from the orbital plane, 0 and r is uniquely determined. In particular (t0, r0) and (tr,, r) conditions, despite the r, distance from the initial orbit is small (as previously mentioned is not up several points), the need is and the speed of pulse o p0 is the same order of magnitude, this time, the movement of the spacecraft no longer meet the C-W equation close assumptions derived from the speed pulse cw performance equation is infinite. 5 Multi-pulse orbit of the fuel consumption is not an optional point example in Figure 3 when the number of pulses N> 2, by (9) △ solution identified is not unique, then the solution can be optimized, but also on Ⅳ pulses f applied to optimize the time. Due to space relations, optimization problem here is not discussed in detail, describes only some of the conclusions for reference. (1) In general, when the total time to complete the transfer orbit Q (tf-t0) is fixed,[link widoczny dla zalogowanych], increase the number of pulses orbit is not significant fuel savings. Especially when (tj-a t0) when the orbital period is less than 04, on t (i = 1,2 ..., N) is always the result of optimization of multi-pulse double pulse orbit into orbit, the two-pulse orbit of least fuel. (2) multi-pulse orbit orbit trajectory to optimize and improve the orbit accuracy. By controlling the intermediate points can make the orbit trajectory in the desired range. If you want to orbit the last paragraph of the pulse is small (the last paragraph of the preceding pulse can be used to compensate for the orbit error), you can optimize the indicators to the larger weighting coefficients. A D r Spacecraft Engineering Volume 7 6 Conclusion In this paper 0w equation is derived based on the general algorithm for multi-pulse orbit. Made under the conditions of dual-pulse orbit \Finally, multi-pulse and double pulse orbit orbit were compared. Methods provided in this article applies to any case cw multi-pulse orbit calculations. The proposed \ More articles related to topics：