Autonomous space flight system and planetary lander for executing a discrete landing sequence to remove unknown navigation error, perform hazard avoidance and relocate the lander and method

US7967255B2 · kind B2 · utility

Assignee

• Raytheon Company · US

Inventors

• James N. Head · Tucson, US
• Gregory V. Hoppa · Hampstead, US
• Thomas Gardner · Anoka, US
• Karen I. Tsetsenekos · Tucson, US
• Stephen M. Dolfini · Tucson, US
• Tomas Svitek · San Luis Obispo, US
• Karleen Seybold · Tucson, US

Key dates

• Filing date: Jul 24, 2007
• Grant date: Jun 28, 2011
• Expiry date: Jun 6, 2030

Classification

• Technology area (CPC B): Performing Operations; Transporting
• CPC primary: B64G1/1071
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

An autonomous unmanned space flight system and planetary lander executes a discrete landing sequence including performing an initial velocity braking maneuver to remove velocity at altitude, coasting during which the planet surface is imaged and correlated to reference maps to estimate cross-track and along-track navigation errors and one or more lateral braking maneuvers are performed to reduce cross-track navigation error, and performing a terminal velocity braking maneuver(s) to reduce the along-track braking maneuver and remove the remainder of the velocity just prior to landing. A bi-propellant propulsion system provides a very high T/M ratio, at least 15:1 per nozzle. Short, high T/M divert maneuvers provide the capability to remove cross-track navigation error efficiently up to the maximum resolution of the reference maps. Short, high T/M terminal velocity braking maneuver(s) provide the capability to remove along-track navigation error to a similar resolution and remove the remaining velocity in a very short time window, approximately 3-15 seconds prior to touchdown. The propulsive efficiency frees up mass which can be allocated to a fuel to remove the unknown navigation er…