Attachment A.1 Trajectory Requirements.pdf
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- Attached to
- 80KSC020R0003 - CAPSTONE - Cislunar Autonomous Positioning System Technology Operations and Navigation Experiment - Launch Service Federal contract opportunity
- Solicitation number
- 80KSC020R0003
About this file
This solicitation requests proposals for launch services to place a spacecraft into cislunar orbit. NASA's Kennedy Space Center is seeking offers for launch vehicle services capable of delivering a 37kg spacecraft to a 160km x 1,330,000km orbit at 30 degrees inclination with 3-sigma dispersions of less than 1 degree in characteristic energy and 10 degrees/second in tipoff rates. Proposals are due by the date and time specified in the solicitation document. The launch period is daily and the spacecraft has no constraints on launch opportunities, thermal requirements, or separation attitude that would impact the launch vehicle mission design. Following spacecraft separation, launch vehicle hardware must not recontact the spacecraft.
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CAPSTONE ATTACHMENT A.1 – Trajectory Requirements 80KSC020R0003
Launch Opportunities The launch vehicle (LV) shall be capable of supporting a launch attempt on any day within the launch period for which the mission design closes.
Reference Mass The reference mass of the spacecraft (SC) is 37 kg. This consists of the 25 kg separating SC, a
9.2 kg dispenser, and 8% margin.
Reference Mission Target Orbit Requirements The LV shall place the spacecraft into an orbit at the Target Interface Point (TIP) with the parameters shown in Table 1.
Table 1: Injection Target Orbit Parameters at TIP
Parameter Value 3-Sigma Dispersion
TIP Time(1) Daily Varying (UTC Time) N/A
Characteristic Energy (C3)(1) <= -0.6 km2/s2 ± 0.1 km2/s2
Argument of Perigee(1) Daily Varying (-20/+20 deg or 160/200 deg)
± 1.0 deg
Right Ascension of the Ascending Node (RAAN) (1)
Daily Varying (0/360 deg)
± 1.0 deg
Inclination >8 deg ± 1.0 deg
Notes:
(1) The targets and TIP time will vary depending on the result of the LV solution. The values and ranges provided reflect a 160 km x 1,330,000 km injection orbit at an inclination of 30 deg.
(2) These targets and dispersion values are preliminary. The final analyses and interfaces shall be developed with the LV.
(3) The LV target orbit parameters shall be defined using the constants defined by the World Geodetic System 1984 (WGS-84).
CAPSTONE ATTACHMENT A.1 – Trajectory Requirements 80KSC020R0003
Mission Thermal Requirements The SC has no thermal requirements that impact the LV mission design nor are there any Sun angle constraints imposed on the LV by the SC mission design.
Separation Attitude The SC has no requirement on the orientation of the LV for separation of the SC.
Tipoff Rates At loss of contact between the LV and the SC, the total SC body rate induced by the LV shall not exceed 10 deg/sec.
Note: Total SC body rate is defined as the RSS of the Xsc, Ysc, and Zsc body rates.
Mission Duration The SC has no requirement on the LV mission duration.
Post SC Separation Following SC separation, the LV hardware shall not recontact the spacecraft.
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