Satellite launch system

Abstract

A system for launching aerospace payloads includes a wingless, unmanned modified lifting body spacecraft (100), with a payload compartment in the forward section of the spacecraft. The spacecraft is propelled by hybrid rockets clustered in the aft section of the spacecraft. Reaction control system (RCS) modules control the flight path and its associated avionics hardware and software. This system also includes a carrier aircraft (200) configured to air-launch the spacecraft. The carrier aircraft includes a flight operations control system, which monitors the spacecraft's payload and monitors and controls launch and flight operations of the spacecraft. A ground-based mission control system monitors and controls the spacecraft's payload and monitors and controls the launch and flight operations of the spacecraft.

Claims

1. A method for launching payloads, comprising: air-launching, from a carrier aircraft, a spacecraft storing a payload in a payload bay, wherein the spacecraft is unmanned; remotely controlling a flight path of the spacecraft via rockets controlled by a reaction control system (RCS); stabilizing the spacecraft via chines, wherein the chines comprise wye-shaped stabilizers; and launching the payload from the spacecraft.

2. The method of claim 1, further comprising, from a remote, ground-based mission control system, at least one of monitoring the payload, controlling a launch, controlling flight operations of the spacecraft, or controlling flight operations of the payload.

3. The method of claim 1, wherein the payload is a satellite.

4. The method of claim 1, wherein controlling the flight path comprises adjusting, by the reaction control system (RCS), at least one of a pitch, roll, yaw, or translation of the spacecraft.

5. The method of claim 1, wherein the spacecraft comprises composite panels encasing rockets of the spacecraft, and a payload bay.

6. The method of claim 5, further comprising separating one or more composite panels from the spacecraft to release the payload bay.

7. The method of claim 6, further comprising activating pyrotechnical charges to separate the one or more composite panels from the spacecraft.

8. The method of claim 1, further comprising providing thrust to the spacecraft via Stage 01 boosters vertically centered on a horizontal plane of the spacecraft.

9. The method of claim 8, further comprising activating the Stage 01 boosters after air-launching the spacecraft.

10. The method of claim 8, further comprising jettisoning the Stage 01 boosters, and providing thrust to the spacecraft via Stage 1 boosters positioned along the horizontal plane of the spacecraft.

11. The method of claim 10, further comprising jettisoning the Stage 1 boosters, and providing thrust to the spacecraft via Stage 2 boosters.

12. The method of claim 11, wherein the Stage 2 boosters are centrally positioned on the horizontal plane of the spacecraft, and a vertical plane of the spacecraft.

13. The method of claim 1, wherein the spacecraft wherein the rockets are hybrid rockets encased within an aerodynamic shell.

14. The method of claim 13, wherein controlling the spacecraft comprises monitoring and controlling exhaust flow from the rockets.

15. The method of claim 5, wherein at least one arm of the wye is canted outboard from a horizontal plane, and wherein a horizontal arm of the wye is fitted with elevons.

16. The method of claim 1, further comprising controlling, from a flight operations control system in the carrier air craft, air-launch and flight operations of the spacecraft.

17. The method of claim 1, wherein air-launching the spacecraft comprises simultaneously decoupling physical connection points between the carrier aircraft and the spacecraft.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is an exterior plan view of the LB-1 spacecraft (100) of the present invention.

(2) FIG. 2 is an exterior elevation view of the LB-1 spacecraft of the present invention.

(3) FIG. 3 is a front exterior view of the LB-1 spacecraft and the carrier aircraft (200).

(4) FIG. 4 is a detail plan view of the LB-1 spacecraft of the present invention.

(5) FIG. 5 is a detail elevation view of the LB-1 spacecraft of the present invention.

(6) FIG. 6 is a section at line A-A of the LB-1 spacecraft of the present invention.

(7) FIG. 7 is a plan view of conventional booster detail of the LB-1 of the present invention.

(8) FIG. 8 is a plan view of positioning and attachment of said LB-1 spacecraft of the present invention.

DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS

(9) All illustrations of the drawings are for the purpose of describing illustrative embodiments and are not intended to limit the scope of the present invention.

(10) The present invention provides a system for launching satellites, including small-sats, mini-sats, nano-sats, medical and scientific experiments, suborbital, orbital and other aerospace payloads, including a modified and optimized existing carrier aircraft, a streamlined, unmanned rocket-propelled lifting body spacecraft (100), air launched from said carrier aircraft (200) and containing in addition to its own propulsion, the payload, staging, propulsion and insertion rocketry necessary to the mission and the provisions for protecting said payload during loading, fueling, transit to and mating with said carrier aircraft, towing, taxiing, conventional takeoff from the runway, climb and cruise to the selected launch point (LP) and high altitude release, as well as the tracking, navigation and control hardware, software and other equipment to effect a safe, reliable and affordable delivery service, including:

(11) FIGS. 1, 2, 3 depict exterior views of LB-1, an unmanned, rocket-powered, wingless lifting body spacecraft 100, assembled of commercially available composite rocket boosters, complete with solid or hybrid fueled motors and strapping hardware. The spacecraft's lifting body characteristics are designed to mitigate lift and altitude losses at the horizontal release maneuver (HRM) and its wingless profile allows attachment between the engines and landing gear of the carrier aircraft 200 (as shown in FIG. 3, at the lower fuselage 7). Joined at chine lines 1A & B, streamlined airfoils of carbon/composite form the nose cone, 2A & 2B, and main body fairings 3A & 3B to create a strong, lightweight covering and provide a lift factor of approximately 65 pounds per square foot. Reference number 3AA (FIG. 3) illustrates an attachment fairing. Mid-body horizontal chines 1A & 1B on each side gradually widen aft of the nose cone from 2 to 3 feet, terminating in upper and lower wye stabilizers 4A & 4B canted outboard 60 degrees from the horizontal and fitted with split elevons 5A & 5B to maintain roll control in the atmosphere. Additionally, the aft chines are fitted with split horizontal elevons for pitch control and use as speed brakes.

(12) The spacecraft's body cross section may be described as a flattened ellipse with a longitudinally placed, laterally centered conventional 2/3-stage rocket booster flanked by symmetrical pairs of propellant boosters of decreasing diameters and a wide, tapering nose cone to establish the desired cross-sectional airfoil.

(13) Four thrusters 6A & 6B (FIGS. 3 and 5) have been provided near the forward end of the upper and lower outboard boosters to increase stability during pitch-up. To avoid waste of Stage 1 thrust, small outboard boosters designated Stage 01 will be ignited to accomplish the pitch-up maneuver prior to Stage 1 ignition. (See FIGS. 4 and 7.) It is foreseen that this combination along with the aforesaid improvement in lift will result in a considerably smoother, more controlled and economical spacecraft rotation.

(14) FIGS. 4, 5, 6: Carrier aircraft belly vertical clearance 7 and landing gear fore and aft clearance 7A & 7B are shown with LB-1 mounted. Reference number 7C indicates the coupling keel and 7D the mounting snubbers. The payload bay is at 9, and potential carrier aircraft hard point connections at 10. (See FIG. 4.) The arrangement of boosters permitting maximum opportunity to accommodate various loading options and combinations of payload types is shown in relation to stages. The preferred embodiment provides that the rocket casings at 11 (FIG. 6) may be truncated at the firewall along section line A-A and the entire nose of the spacecraft or selected portions thereof may be utilized.

(15) FIG. 7 depicts a plan view showing a conventional booster display at 13. To enable and control the cost of this quick-change facility it is planned that several firewall/payload plate options will be made available at loading sites.

(16) FIG. 8 provides a positioning diagram for mating of the LB-1 utilizing the carrier aircraft hard point connections 10. An outline of the transport dolly chassis 15 demonstrates lead-in guidance and critical component clearances. A low, wheeled concave dolly shaped to accept, center and support the convex lower spacecraft half for precisely placing the propellant boosters and to support the same during transit, servicing, fueling, applying the upper spacecraft half and towing under the carrier aircraft for mounting and supplying battery power to said spacecraft components.

(17) Facilities for the monitoring and audible alarm of latching/sealing mechanisms, rising temperatures, leakage of oxidizer, suppression of fire and other safety measures which may be provided at the spacecraft, and the carrier aircraft cockpit and launch control stations, separate from similar systems in the carrier aircraft.

(18) Attachments and adaptors on the carrier aircraft and the spacecraft to enable the quick attachment/release of the spacecraft may also be provided.

(19) Facilities in the carrier aircraft and on the ground to remotely control the spacecraft as a mission-abort/reentry vehicle may also be provided.

(20) Computerized Operations Specifications and irregular and emergency procedures and checklists to be performed by crew members will govern in all phases of the mission.

(21) The LB-1 spacecraft is scalable over the range of potential carrier aircraft to suit the requirements of smaller or larger payloads.

(22) The LB-1 is designed for polar and equatorial launch missions.

(23) Although the invention has been described in terms of its preferred embodiment, it is to be understood that many other possible modifications and variations can be made without departing from the spirit and scope of the invention. Launch preparations, including assembling, loading, and attaching the LB-I to the aircraft, include, in the following order: 1. Lower body fairing, chines, stabs. 2. Thrust plate. 3. Firewall 4. Stage 2/3 booster. 5. Stage I boosters & straps. 6. Stage OI boosters & straps. 7. Left & Right Thrusters. 8. Payload plate. 9. Upper Body fairing, chines, stabs. 10. Secure cargo in Payload Bay. 11. Place nose cone, secure & check all fasteners. 12. Align LB-I beneath carrier aircraft. 13. Complete LB-I attachment checklist. 14. Attach LB-I to carrier aircraft & secure.

(24) Flight operations, including towing, taxiing, takeoff, and flight, require the following: 1. All towing operations with LB-I attached shall be conducted in radio contact with qualified ground crew ahead and behind the carrier aircraft and ground level visibility of at least 3 nautical miles. 2. Prior to engine start all landing gear and tires shall be checked for damage or irregularities and the captain advised. 3. Immediately prior to every take-off with LB-1 attached the ground crew shall scan the takeoff runway for foreign objects and remove any debris advising the captain by radio that the runway surface is safe for takeoff. 4. When the captain receives the ground crew disconnect salute his acknowledgement will indicate his acceptance of aircraft, spacecraft and runway surface as suitable for the launch mission subject to tower takeoff clearance, and he will change frequency accordingly. The ground crew will remain clear of the taxiway but in the general area until the takeoff is complete. 5. Special procedures will govern LB-1 flight operations, including more restrictive takeoff weather minimums for ceiling, visibility, crosswind, runway clutter and precipitation. Also rejected takeoff, fuel dumping, primary and alternate launch point (LP) criteria, will be more critical, especially tropopause weather, particularly winds, which can be in excess of 200 knots and turbulence which may be extreme. Alternate launch points (LPs)/altitudes will be filed for every mission. 6. Staging will generally be conventional for the launch type being conducted, however all specifications, exceptions, alternate launch points (LPs) and other advisories will be included on the flight plan and updated automatically or upon request. 7. In the event of a failure in a primary launch system or component, a joint decision will be reached between the captain and the launch coordinator as to whether a safe/successful launch can be achieved with a standby system or component or hand-flown maneuver, or whether the load should be returned to base or jettisoned, and if either of the latter, whether carrier aircraft fuel dumping or another safer course of action is indicated. 8. Although air-launch has demonstrated an excellent safety record in both manned and unmanned missions, payload insurance continues a major driver of launch cost, therefore every effort should be extended to design equipment and procedures to the highest standards of safe operation.