Launch window and translunar, lunar orbit, and transearth trajectoryplanning and control for the Apollo 11 lunar landing mission

Berry, Ronald L.

doi:10.2514/6.1970-24

Cited by 31 publications

(50 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The free return phase of the hybrid trajectory has the same capability as described previously about the free return trajectory. For the free return trajectory, Berry pointed out that the range of lunar approach inclination is constrained within approximately 10° of the lunar equatorial plane [3], as shown in Figure 3. In the figure, N denotes the intersection node of the spacecraft's approach trajectory with the lunar equatorial plane.…”

Section: Types Of Abort Trajectoriesmentioning

confidence: 99%

See 1 more Smart Citation

Review on abort trajectory for manned lunar landing mission

Huang

Wang

2010

Sci. China Technol. Sci.

View full text Add to dashboard Cite

Abort trajectory is a passage that ensures the astronauts to return safely to the earth when an emergency occurs. Firstly, the essential elements of mission abort are analyzed entirely based on summarizing the existing studies. Then, abort trajectory requirement and rational selection for different flight phases of typical manned lunar mission are discussed specifically. Considering a trade-off between the two primary constrains of an abort, the return time of flight and energy requirement, a general optimizing method for mission abort is proposed. Finally, some suggestions are given for China's future manned lunar landing mission. manned lunar landing, mission abort, trajectory design, free return trajectory Citation:

show abstract

Section: Types Of Abort Trajectoriesmentioning

confidence: 99%

“…American scholars have studied the abort for manned lunar mission as many as the normal mission [2][3][4][5][6][7][8][9][10][11][12][13][14][15], which will be described in detail below. After the CE-1 was successfully implemented, China's manned lunar landing program will also be accomplished consequentially in the near future.…”

Section: Introductionmentioning

confidence: 99%

Review on abort trajectory for manned lunar landing mission

Huang

Wang

2010

Sci. China Technol. Sci.

View full text Add to dashboard Cite

show abstract

“…Limited by the capability of the spacecraft, the trans-lunar time t 1 and return time t 2 can not be too long, and the TLI v A and LOI v C are also restricted. They should satisfy 1 1…”

Section: Initial Orbit Designmentioning

confidence: 99%

“…Many analysis of FRO were done in the Apollo mission [1][2][3][4][5][6]. But the design method and computation capability in the Apollo era were quite different from now, and the studies were mainly focused on the mission analysis, the detailed design models and methods were not given in the references.…”

Section: Introductionmentioning

confidence: 99%

Free return orbit design and characteristics analysis for manned lunar mission

Peng

Shen

2011

Sci. China Technol. Sci.

View full text Add to dashboard Cite

A circumlunar free return orbit design model that satisfies manned lunar mission constraints is established. By combining analytical method with numerical method, a serial orbit design strategy from initial value design to precision solution is proposed. A simulation example is given, and the conclusion indicates that the method has excellent convergence performance and precision. According to a great deal of simulation results solved by the method, the free return orbit characters such as accessible moon orbit parameters, return orbit parameters, transfer delta velocity, etc. are analyzed, which can supply references to constitute manned lunar mission orbit scheme. manned lunar mission, free return orbit, orbit design, orbit characters Citation:Peng Q B, Shen H X, Li H Y. Free return orbit design and characteristics analysis for manned lunar mission.

show abstract

“…There are many papers which deal with the translunar trajectory of the actual lunar missions [1][2][3][4][5][6][7][8] . The papers show the results of the trajectory design considering the practical conditions, requirements, and constraints of the respective missions.…”

Section: Introductionmentioning

confidence: 99%

Study on the Characteristics of Two-burn Translunar Trajectory

Kawakatsu

2007

Trans. JSASS Space Tech. Japan

View full text Add to dashboard Cite

In this paper, the translunar trajectory of the simple sequence is investigated. The trajectory discussed in this paper is a two-burn ballistic trajectory from the low earth parking orbit to the low lunar orbit. The problem is practical in that the geometric relation from the launch site to the moon is fully considered. The paper includes three subjects. First is the structure of the problem and the solution space. The problems are defined and the solutions are grouped by the properties of the lunar transfer sequence. Second are the characteristics of optimal solutions. The topics discussed are the transition of the required velocity increment based on the launch date, and the difference according to the property of the lunar transfer sequence. Third is the sensitivity analysis of a number of items to the deviation of the parameters from the optimal solution.

show abstract

Launch window and translunar, lunar orbit, and transearth trajectoryplanning and control for the Apollo 11 lunar landing mission

Cited by 31 publications

References 0 publications

Review on abort trajectory for manned lunar landing mission

Review on abort trajectory for manned lunar landing mission

Free return orbit design and characteristics analysis for manned lunar mission

Study on the Characteristics of Two-burn Translunar Trajectory

Contact Info

Product

Resources

About