초록 ▼

Disclosed is a space vehicle, such as a satellite, the vehicle including: at least one equipment-carrying module for carrying equipment of the vehicle; at least three posts extending at least partially in the same longitudinal direction and on the periphery of the equipment-carrying module, each pos

Disclosed is a space vehicle, such as a satellite, the vehicle including: at least one equipment-carrying module for carrying equipment of the vehicle; at least three posts extending at least partially in the same longitudinal direction and on the periphery of the equipment-carrying module, each post being provided with at least one releasable locking device; and a reinforcing structure which rigidly connects each post transversely to at least two other posts.

대표청구항 ▼

1. A spacecraft (1, 100) intended to be put into orbit around a planet, the spacecraft (1, 100) comprising: at least one equipment carrying module (2, 102), for supporting the spacecraft (1, 100) equipment;at least three posts (12, 112) extending at least partially in a same longitudinal direction (

1. A spacecraft (1, 100) intended to be put into orbit around a planet, the spacecraft (1, 100) comprising: at least one equipment carrying module (2, 102), for supporting the spacecraft (1, 100) equipment;at least three posts (12, 112) extending at least partially in a same longitudinal direction (A) and at the periphery of the equipment carrying module (2, 102), each post (12, 112) being provided with at least one releasable locking device (15, 115) which may have two states: a locked state, wherein the locking device (15, 115) is attached to an additional locking device (15, 115),an unlocked state, wherein the locking device (15, 115) is released from any other locking device (15, 115);a reinforcing structure (16, 116) which rigidly connects each post (12, 112) transversely to at least two other posts (12, 112). 2. The spacecraft (1, 100) according to claim 1, wherein there are three posts (12, 112) and they are distributed on the vertices of an equilateral triangle. 3. The spacecraft (1, 100) according to claim 1, wherein there are four posts (12, 112) and they are distributed on the vertices of a parallelogram. 4. The spacecraft (1, 100) according to claim 1, wherein each releasable locking device (15, 115) comprises a magnetic member. 5. The spacecraft (1, 100) according to claim 1, wherein each releasable locking device (15, 115) comprises a pyrotechnic member. 6. The spacecraft (1, 100) according to claim 1, wherein each post extends longitudinally between two ends (13, 14), each end (13, 14) being provided with a locking device (15, 115). 7. Method of assembling at least two spacecrafts (1, 100) according to claim 1, comprising the steps of: positioning the at least two spacecrafts (1, 100) such that the posts (12, 112) of a first spacecraft (1, 100) extend at least partially in a same longitudinal direction as the posts (12, 112) of the second spacecraft (1, 100);cooperating each locking device (15, 115) of the first spacecraft (1, 100) with a locking device (15, 115) of the second spacecraft (1, 100);switching to the locked state of the locking devices (15, 115) of the first spacecraft (1, 100) on the locking devices (15, 115) of the second spacecraft (1, 100). 8. The spacecraft (1, 100) according to claim 1, wherein the reinforcing structure (16, 116) comprises reinforcing members in the form of legs (17, 117), the number of which corresponds to at least the number of posts (12, 112), each leg (17, 117) being attached between two posts (12, 112). 9. The spacecraft (1, 100) according to claim 8, wherein the reinforcing legs (17, 117) are connected in pairs by shear consolidating members (19). 10. The spacecraft (1, 100) according to claim 8, wherein the legs (17, 117) are combined with the equipment carrying module (2, 102) walls, the walls forming a support for the spacecraft. (1, 100) equipment. 11. The spacecraft (1, 100) according to claim 10, wherein the reinforcing legs (17, 117) are connected in pairs by shear consolidating member (19). 12. The spacecraft (1, 100) according to claim 1, wherein the reinforcing structure (16, 116) comprises reinforcing members in the form of legs (17, 117), the number of which corresponds to at least the number of posts (12, 112), each leg (17, 117) being attached to one of the posts (12, 112) and to a single attachment center (C). 13. The spacecraft (1, 100) according to claim 12, wherein the reinforcing legs (17, 117) are connected in pairs by shear consolidating members (19). 14. The spacecraft (1, 100) according to claim 1, wherein each post (12, 112) is provided with two releasable locking devices (15, 115). 15. Stack of spacecraft (1, 100) according to claim 14, comprising at least two spacecrafts (1, 100) secured together, the at least one releasable locking device (15, 115) of each post (12, 112) of a first spacecraft (1, 100) being in locked position with a locking device (15, 115) on a post (12, 112) of the second spacecraft (1, 100), the posts (12, 112) for each spacecraft extending in a same longitudinal direction (A), the stack further comprising a device for controlling the state of the locking devices (15, 115). 16. Stack of spacecrafts (1, 100) according to claim 15, wherein the spacecrafts (1, 100) are satellites comprising an Earth face (7, 104) and an anti-Earth face (8, 103), the Earth and anti-Earth faces being oriented in the longitudinal direction (A) of the posts (12, 112). 17. Stack of spacecrafts (1, 100) according to claim 15, wherein the spacecrafts (1, 100) are satellites comprising an Earth face (7, 104) and an anti-Earth face (8, 103), the Earth (7, 104) and anti-Earth (8, 103) faces being oriented in a direction transverse to the posts (12, 112). 18. Spacecraft (1, 100) launcher (20, 120, 220), the launcher comprising a spacecraft interface structure (21, 121, 221) and at least one first stack of spacecrafts (1, 100) according claim 15, a first locking device (15, 115) for each post (12, 112) of the first spacecraft (1, 100) being in the locked state on a locking device (15, 115) of the second spacecraft (1, 100), the second locking device (15, 115) of each post (12, 112) of the first spacecraft (1, 100) being in the locked. state on the spacecraft interface structure (21, 121, 221). 19. Method for dropping spacecrafts (1, 100) by means of a launcher (21, 121, 221) according to claim 18, comprising a step of separation between. a spacecraft (1, 100) to be dropped and a spacecraft (1, 100) intended to remain in the launcher by putting into the unlocked state the locking devices (15, 115) between the two spacecrafts (1, 100) so as to release a single spacecraft (1, 100). 20. Method for dropping spacecrafts (1, 100) by means of a launcher (21, 121, 221) according to claim 18, comprising a step of separation between a group of spacecrafts (1, 100) to be dropped and one spacecraft (1, 100) intended to remain in the launcher by putting into the unlocked state the locking devices (15, 115) between a spacecraft (1, 100) from the group to be dropped and the spacecraft (1, 100) intended to remain in the launcher (20, 120, 220), in order to drop the group of spacecrafts (1, 100).