Device to select astronomic objects of surveillance from orbital spacecraft

FIELD: aviation.

SUBSTANCE: device to select astronomic objects of surveillance from an orbital spacecraft (SC), includes a globe with an applied sky map, two rings covering the globe, centres of which are matched with the centre of the globe, an element with a circular contour, the projection of which to the surface of the globe forms a circumference that limits the segment of the globe surface with an angle of semi-opening counted from the direction from the centre of the globe to the centre of the specified segment of the globe surface, equal to the angle of semi-opening of a disc visible from the SC in the planet located in the centre of the near-circular orbit of the SC, and an arc element connected with the specified element with the circular contour. The first ring is fixed above points of globe poles with the possibility to rotate a ring around the axis of globe rotation. The second ring is fixed on the first ring. The plane of the second ring makes an angle with the plane of the globe equator equal to the angle of SC orbit inclination. In addition the size of the arc element arc measured from the centre of the globe is equal to 180°-Q, where Q - angle of semi-opening of the planet disc visible from the SC orbit. The arc element with its end point is rigidly connected with the edge of the element with the circular contour. The arc element and element with the circular contour are made as detachable and equipped with a facility of their fixation on the globe in positions, in which the free end point of the arc element and the centre of the element with circular contour are at the same diameter of the globe.

EFFECT: expansion of device functional capabilities.

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The invention relates to the field of space technology and can be used for the identification and selection of astronomical objects for observations from orbiting SPACECRAFT), moving in a near-circular orbit. This solution can also be used as a visual aid and a training device for navigation, celestial mechanics, mechanics of space flight.

Known the globe [1], p.93-97, which can be used to identify and select objects observations performed with the AC. The disadvantage of this device is the lack of elements that can display information about the orbit and track the SPACECRAFT.

A device for selection of astronomical objects observations from orbiting SPACECRAFT [2], including star globe, two rings, spanning the globe and the two ring element the first ring fixed to the poles of the globe to rotate the first ring around the axis of rotation of the globe, and a second ring mounted on the first ring with the possibility of rotation of the second ring to the position in which the plane of the second ring makes with the plane of the equator, the angle equal to the inclination of the orbit, and the annular elements mounted over the globe with its opposite sides by one or more arcs connecting these elements with the ring which. The device allows you to define the objects of the celestial sphere, observable with KA for all round orbit.

The closest analogues adopted for the prototype, is a device for selection of astronomical objects observations from orbiting SPACECRAFT [3], which includes the globe coated with a map of the sky, two covering the globe rings, the centers of which are aligned with the center of the globe, the element in the form of half rings mounted on the second ring with the possibility of moving element in the form of half rings along the second ring, and an element with a circular contour, the projection of which on the globe surface forms a circle bounding the segment of the surface of the globe with angle polarstar measured from the direction of the center of the globe at the centre mentioned segment surface globe, equal to the angle of polarstar visible with the AC drive of the planet, around which turns moving in a near-circular orbit of the SPACECRAFT during this element with a circular contour fixed my point, the projections of which on the globe surface coincides with the center of the mentioned segment of the surface of the globe, in the end point of the element in the form of half rings, the first ring attached above the points of the poles of the globe with the possibility of rotation of the ring around the axis of rotation of the globe, and a second ring secured to the first ring at the hands of intersection of the first ring with the plane of the equator of the globe, with the possibility of rotation of the second ring to the provisions in which the plane of the second ring makes with the plane of the equator of the globe angle equal to the inclination angle of the orbit of the SPACECRAFT.

Working with the device is as follows.

The second ring rotates relative to the first ring in a position in which the second ring makes with the plane of the equator of the globe angle equal to the inclination angle of the orbit. Then turn the globe around its axis of rotation set the globe in a position in which the point of intersection of the rings and is located above the point of the equator with longitude equal to the value of the longitude of the ascending node of the considered orbits orbit. The line of projection of the second circle on the surface of the globe will show line marks the radius-vectors of the SPACECRAFT at the globe during the loop orbit. By moving the element in the form of half rings along the second ring combine extreme point of the element in the form of half rings with dots of the second circuit corresponding to the various provisions of the SPACECRAFT along this spiral orbit. The other extreme point of the element in the form of half rings will be located above the point of the track on the celestial sphere in the direction from the SPACECRAFT to the center of the planet. Element with a circular path, the center of which is fixed to the extreme point of the element in the form of a half ring, cover for the globe's surface area, which in the current time is not available OBS is the observed SPACECRAFT. Astronomical objects on the rest of the surface of the globe, will be available at the current time observation SPACECRAFT.

To determine the areas of orbits, for the astronomical object is available or not available for monitoring SPACECRAFT, it is necessary to perform multiple moving element in the form of half rings with a fixed element with a circular path along the second ring and through trial builds to determine the position of the SPACECRAFT, when considering the astronomical object is covered or not covered by the element with a circular contour, which corresponds to the facts, respectively, unavailability and availability considering a specific astronomical object observation at this stage of the orbit of the SPACECRAFT. While performing all these manipulations with the device though, and allows you to determine the availability and unavailability considered astronomical object observation of each SPACECRAFT location, but does not clearly show the total area of visibility and invisibility of this astronomical object in this orbit orbit.

The device prototype has a major drawback - for all moments of time in which a given astronomical object accessible and inaccessible to observation, it is necessary to perform multiple man is palatii with the device, moreover, the device does not have the ability display the total of the areas of visibility and invisibility of each specific astronomical object.

The task of the proposed device is an expansion of the functionality of the device by providing a visual display on the simulated orbit orbit total zones orbits, on which the available and unavailable observation SPACECRAFT any particular astronomical object.

The technical result is achieved in that in a device for selection of astronomical objects observations from orbiting spacecraft, including the globe coated with a map of the sky, two covering the globe rings, the centers of which are aligned with the center of the globe, an element with a circular contour, the projection of which on the globe surface forms a circle bounding the segment of the surface of the globe with angle polarstar measured from the direction of the center of the globe at the center of the mentioned segment of the surface of the globe, equal to the angle of polarstar visible from the spacecraft disk located in the center of the near-circular orbit of the spacecraft on the planet, and arc element connected with the said element with a circular loop, with the first ring attached above the points of the poles of the globe with the opportunity the treatment of ring around the axis of rotation of the globe, and the second ring mounted on the first ring and the plane of the second ring makes with the plane of the equator of the globe angle equal to the inclination angle of the orbit of the spacecraft, wherein optionally the size of the arc of the arc element, measured from the center of the globe, equal to 180°-Q, where Q is the angle polarstar visible from orbit spacecraft disk planet, this arc element of its end-point is rigidly connected to the edge of an element with a circular contour, and arc element and rigidly connected therewith element with a circular contour are removable and provided with a means of fixing the arc element and the element with a circular the contour on the globe in specified positions, in each of which the free end point of the arc element and the center element with a circular contour are located on the same diameter of the globe.

In addition, in the device for selection of astronomical objects with orbital spacecraft means for fixing the arc element and the element with a circular contour on the globe can be in the form of clamping device, placed in the free end point of the arc element and containing a movable pin-retainer mounted with the possibility of moving it to the center of the globe.

The device illustrated in figures 1, 2. Figure 1 shows in the D. the proposed device. Figure 2 is a diagram explaining the choice of values of the angle polarstar spherical segment of the globe, a limited projection of the contour element with a circular path.

Figure 1 is a typed notation:

1 - globe coated with a map of the sky;

2, 3 - first and second rings, respectively;

4 - arc element;

5 - element with a circular contour;

6 - clamping device;

7 - line of the equator of the globe;

8 - line of the Meridian passing through the point of the ascending node of the orbit;

9 - line projection of the second ring 3 on the globe;

10 - line projection of the contour element with a circular path 5 on the globe;

11 is a spherical segment of the globe bounded by the projection of the contour element with a circular contour 5;

12 - element stand globe, which is a continuation of the axis of rotation of the globe;

13 - the technological gap in the element with a circular contour 5;

14 - pin-retainer;

15 - elastic element;

And the pole of the globe;

From the point of intersection of the first and second rings;

D is the point on the equator, corresponding to the ascending node of the orbit of the SPACECRAFT.

F₁- the end point of the arc element 4, in which the anchor member with a circular contour 5;

F - free end point of the arc element 4;

V - center element with a circular contour 5.

Figure 2 additionally shows:

G - the celestial sphere;

P - surface of the sphere approximating the surface of the planet, around which turns the AC;

M - this astronomical object on the celestial sphere;

K - point of the celestial sphere diametrically opposite the considered astronomical object;

O_p- the center of the planet;

O₁O₂position AC;

K₁, K₂traces of the radius-vector of the SPACECRAFT on the celestial sphere;

E, E₁E₂points visible from the AC horizon of the planet;

EE₁- visible from the AC drive of the planet;

Q - angle polarstar visible with the AC drive of the planet.

Each time the direction from the SPACECRAFT to the center of the planet opposite to the direction of the radius-vector of the SPACECRAFT. The angle Q is calculated by the formula:

$$Q=\arcsin {\text{(R}}_{\text{p}}{\text{/R}}_{\text{o}}\text{)}\text{, (1)}$$

where R_o=O_pO₁is the radius of the orbit;

R_p=O_pE₁- the radius of the planet.

Provision of KA, the direction from which the object of the celestial sphere makes with the direction from the SPACECRAFT to the center of the planet angle not exceeding the value of the angle Q, the object of the celestial sphere is not visible (closed planet). Thus, the object of the celestial sphere will not be available to observe the structure of these provisions, CA.

The celestial sphere is conceived as a sphere of large radius, in comparison with which the distance between the points O_pand O₁negligible, and in applying to the star globe data points are combined into a single point O, which is the center of the celestial sphere (the center of the globe).

The object of the celestial sphere M inaccessible to observation of the provisions KA, trace the radius vector which is part of the celestial sphere, which is a spherical segment K₁KK₂with the angle polarstar Q and the center of which is the point K located on the celestial sphere diametrically opposite the object of the celestial sphere M of the provisions KA, track radius-vector which is in the rest of the celestial sphere K₁MK₂this object of the celestial sphere M of the observable.

From the diagram presented in figure 2, it follows that the size of the arc of the arc element 4 is equal to the value of:

$$L=180°-Q,\text{(2)}$$

and circuit element with a circular circuit 5 forms a circle, the radius of which is equal to the value of:

$$H=R\cdot \sin Q,\text{(3)}$$

where R is the distance from the points of the contour element with a circular path 5 to the center of the globe 1.

Means for fixing the arc element and the element with a circular contour on the globe can be in the form of the clamping device 6 placed in the free end point of the arc element F and containing a movable pin clamp 14 mounted with the possibility of moving it to the center of the globe 1. The pin-retainer 14 to the center of the globe 1 is provided, for example, between the arc element 4 and the pin-pusher 14 of the elastic element 15. The direction of movement of the pin-retainer 14 under the action of the elastic element 15 is directed into the center of the globe 1.

Optionally, the element with the circular path 5 may be the technological gap 13, which are used when installing the arc element 4 element with a circular contour 5 in set position on the globe 1. The size of the technology gaps 13 corresponds to the size of the structural elements of the globe 12, which may abut the element with a circular path 5 when installed on the surface of the globe 1.

Working with the device is as follows. The second ring 3 rotates relative to the first ring 2 in a position in which the second ring 3 makes with the plane of the equator to Globo, the 7 corner equal to the inclination angle of the orbit. Then turn the globe 1 around the rotation axis set the globe 1 in a position in which the point of intersection of the rings 2 and 3 is located above the point D of the equator with longitude equal to the value of the longitude of the ascending node of the considered orbits orbit. Line 9 projection of the second ring 3 on the surface of the globe 1 will show line marks the radius-vectors of the SPACECRAFT at the globe 1 during the turn of the orbit.

Using the means of fixation of the arc element and the element with a circular contour on the globe fix this situation arc element 4 element with a circular path 5 on the globe 1, wherein the free end point of the arc element F is located directly above the considered astronomical object M When using the clamping device 6, for example, compress the elastic element 15, by moving the pin-retainer 14 in the direction from the center of the globe 1, put the pin-retainer 14 above the point in question astronomical object M, the element with a circular contour 5 is placed diametrically opposite the considered astronomical object M, open elastic element 15, moving the pin-retainer 14 in the direction toward the center of the globe 1. Thus, the clamping device 6 will provide fixation on the globe 1 user-defined position of the arc element is 4 and the element with a circular contour 5.

When the edge of an element with a circular contour 5 "rests" in the structure of the globe 12, the structure of the globe 12 in advance injected into the gap 13 in the element with a circular contour 5.

After installation of the arc element 4 element with a circular contour 5 of the points of intersection of the element with the circular path 5 with the second ring 3 will indicate on the second ring 3 zone round orbit, while in which KA is visible and not visible under consideration astronomical object. The area round orbit, the modeled segment of the second ring 3 located inside an element with a circular path 5, is a zone within which the considered astronomical object inaccessible to observation. The area round orbit, the modeled segment of the second ring 3 located outside the element with a circular path 5, is a zone within which the considered astronomical object accessible to observation.

Describe the technical effect of the invention.

The proposed device extends the functionality of the device by providing a visual display of the simulated second ring 3 turn the satellite orbit, the total areas of revolution, during which the available and unavailable observation SPACECRAFT any particular astronomical object.

The technical result is achieved due to the implementation of the arcs is the first element 4 of the proposed size, the proposed rigid connection of the arc element 4 element with a circular contour 5, perform rigidly connected arc element 4 and element with a circular contour 5 removable, and also due to the introduction of the means of fixation of the arc element and the element with a circular contour on the globe in the proposed provisions.

LITERATURE

1. Handsome B. I. Nautical astronomy. M.: Transport, 1986.

2. RF patent №2339000 from 26.05.2006.

3. RF patent 2420714 on the application 2009125857 from 06.07.2009.

1. Device for selection of astronomical objects observations from orbiting spacecraft, including the globe coated with a map of the sky, two covering the globe rings, the centers of which are aligned with the center of the globe, an element with a circular contour, the projection of which on the globe surface forms a circle bounding the segment of the surface of the globe with angle polarstar measured from the direction of the center of the globe at the center of the mentioned segment of the surface of the globe, equal to the angle of polarstar visible from the spacecraft disk located in the center of the near-circular orbit of the spacecraft on the planet, and arc element connected with the said element with a circular loop, with the first ring fixed above the points of the poles of the globe with the possibility of rotation of the ring around the axis of rotation of the globe, AutoRAE ring mounted on the first ring, moreover, the plane of the second ring makes with the plane of the equator of the globe angle equal to the inclination angle of the orbit of the spacecraft, wherein optionally the size of the arc of the arc element, measured from the center of the globe, equal to 180°-Q, where Q is the angle polarstar visible from orbit spacecraft disk planet, this arc element of its end-point is rigidly connected to the edge of an element with a circular contour, and arc element and rigidly connected therewith element with a circular contour are removable and provided with a means of fixing the arc element and the element with a circular contour on the globe asked the provisions in every one of them free end point of the arc element and the center element with a circular contour are located on the same diameter of the globe.

2. Device for selection of astronomical objects with orbital spacecraft according to claim 1, characterized in that the means for fixing the arc element and the element with a circular contour on the globe is made in the form of the clamping device, placed in the free end point of the arc element and containing a movable pin-retainer mounted with the possibility of moving it to the center of the globe.