Variable surface landing platform (VARSLAP)

• US 8,960,600 B2
• Filed: 02/08/2010
• Issued: 02/24/2015
• Est. Priority Date: 02/08/2010
• Status: Active Grant

• Current Assignee: Raymond George Carreker
• Original Assignee: Raymond George Carreker
• Inventors: Carreker, Raymond George
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Green, Richard R
• Application Number:
  US13/576,830
• Publication Number:
  US 20120298796A1
• Time in Patent Office: 1,842 Days
• Field of Search: 244/100.R, 244/138.R, 244102 R-102 SS, 244104 R-104 LS, 244/108, 244/109, 244/17.17, 244/158.1, 267/69, 267/70, 267/71, 267/73, 267/74, 267/135, 267/166, 267/169, 267/170, 267/174, 267/179
• US Class Current: 244/100.R
• CPC Class Codes: B64G 1/1071 Planetary landers intended for the exploration of the surface of planets, moons or comets
• CPC Class Codes: B64G 1/22 Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• CPC Class Codes: B64G 1/62 Systems for re-entry into the earth's atmosphere; Retarding or landing devices

Abstract

In one embodiment, a variable surface landing platform (VARSLAP) includes a base for contacting a landing surface; at least 3 adjustable struts interconnected with the base, wherein each strut is bisected by a strut actuator-housing, and wherein the at least 3 adjustable struts are interconnected to a main body aerospace craft (MAC); a sensor array on the base; and an attitude determination and control system (ADCS).

Claims

1. A variable surface landing platform (VARSLAP), comprising:

(a) a base for contacting a landing surface;

(b) at least 3 adjustable struts interconnected with the base, wherein each strut is bisected by a strut actuator-housing, and wherein the at least 3 adjustable struts are interconnected to a main body aerospace craft (MAC);

(c) wherein the adjustable struts house a first and second coil springs,

(d) wherein the first coil spring is attached to a first side of a revolving disk located in each of the at least 3 struts and the second coil spring is attached to a second side of the revolving disk,

(e) a sensor array on the base; and

(f) an attitude determination and control system (ADCS).

2. The VARSLAP of claim 1, wherein the adjustable struts have a first position and a second position, the first position being a retracted position and the second position being an extended position.

3. The VARSLAP of claim 1, wherein the base is a rigid-body.

4. The VARSLAP of claim 1, wherein the base is a hollow, circular ring with a convex undersurface.

5. The VARSLAP of claim 1, wherein the ADCS controls the at least three struts, the ADCS receiving an indication that a first one or two of the at least three struts has contacted the landing surface, fully contracting the first one or two of the at least three struts, maintaining the MAC in an orientation perpendicular to a gravitational vector by adjusting the at least three struts until the MAC is at rest.

6. The strut of claim 5 wherein at least one sensor is associated with the strut.

7. The VARSLAP of claim 1, further comprising:

(e) at least one movable transition joint oriented between the base, strut, and MAC mount of the VARSLAP and between the VARSLAP and the MAC

(f) at least one movable transition joint oriented between the VARSLAP and the MAC where no MAC mount is configured, wherein said strut is attached directly to said MAC.

8. The VARSLAP of claim 7, wherein the movable transition joint has three-dimensional freedom of movement.

9. The VARSLAP of claim 1, wherein the adjustable struts house a coil spring.

10. The VARSLAP of claim 1, wherein the revolving disk has a first and second position, in the first position the first and second coil springs are fully extended due to deflection caused by the rotation of the revolving disk, and in the second position the first and second coil springs are retracted.

11. An aerospace craft landing strut, for use with a landing platform for a load, the strut B comprising:

(a) an extendable outer strut body having a hollow center;

(b) a first and second spring; and

(c) a plate oriented inside the hollow center the first spring attached to a first side of the plate, the second spring attached to the second side of the plate, wherein the first and second spring are anchored at the ends of the strut, such that turning of the plate applies a torque to the first and second spring and thereby extends the spring and the strut.

12. The strut of claim 11 wherein an actuator located in the hollow center performs the turning of the plate.

13. The strut of claim 12 wherein the actuator has an involute torsion-lock.

14. The strut of claim 13 wherein the involute torsion-lock includes a solenoid that locks the strut in place.

15. The strut of claim 11 wherein said strut is attached to a support frame wherein said frame is attached to the strut by a movable transition joint.

16. The strut of claim 11 further comprising a power and sensor cable system wherein said cables are directed along the inner circumference of the strut body having a hollow center.