Design and development of spacecraft with outer shell structure heat shielding and built-in, removable excursion modul

Vanalstyne, E. M.

English

NASA Technical Reports Server

3; 547; 3 76 
https://ntrs.nasa.gov/search.jsp?R=19710015958 2020-03-17T03:09:51+00:00Z
W 
BY 
Y 
[ 72)  Inventors T, 0. Paine 
A d ~ ~ ~ t o r  of he National Aeronautics 
aad Space A d ~ ~ ~ r a t i o ~  h respect tom 
~nven~ion f;
Earl M. Van Alstyne, Laguna 
[2 1 ] Appl. No. 895,586 
[22] Filed .IS, 1969 
[45] Patented 15, a970 
1521 OS. CY ........................................................ 24411, 
244/113,244/138 
............................................ B64g 1/55 
............................................ 244/1ss, 
138,113 
[561 References Cited 
UNITED STATES PATENTS 
3,231,219 111966 Young .......................... 244/1(sS) 
3,289,974 1211966 Cohen eta1 ................... 244/1(ss) 
Primary Examiner-Milton Buchler 
Assistant Examiner-Jeffrey L. Forman 
Attorneys-Russell E. Schlorff, Marvin F. Matthews and G. T. 
McCoy 
- 
ABST~AC~: A spacecraft arranged such that it has an 
aerodynamic outer shell which acts as the heat shield. It in- 
cludes an excursion module removably housed within the 
shell, with the module having a retracted landing gear and a 
forwardly thrusting thrust means, such as an engine, at the for- 
ward end thereof and a crew station generally rearward of the 
landing gear. It also includes means for separating the module 
from the shell after separation, whereby the spacecraft can 
then be landed by activation of the thrust means to land the 
vehicle forward end down. 
the module which 
6 . 1 3  shows staging of the module prior to rendezvous; 
a side elevation view, partly in central section, 
showing the module housed within the shell; 
FIG. 3 is a view of the spacecraft shown in FIG. 2, but 
rotated 180” therefrom, and showing the shell jettisoned, the 
landing gear deployed, and the module landed; and 
formance of work under a NASA Contract and is subject to 
the provisions of Section S of the National Aeronautics and 
(72 stat. 435; 42 
U.S.C. 2457). 
is a top plan view of the spacecraft shown in FIG. 3. 
BACKGROUND OF THE INVENTION 
1. Field of the Invention 
This invention relates to a spacecraft having a jettisonable 
such a heat shield together with extendable landing gem 
Refenring now to the various FIGS. 1, and 1A first, a 
11 is shown as it might appear in orbit 
rs traveling with the blunt end rearward 
heat shield. More particularly, it relates to a spacecraft having 15 mother space veh 
mounted inside of the forward end of the shell. 
around the Planet 
For a spacecraft of the type which would be useful for ex- 
ploration of Mars, for example, it is desirable to have an ex- 
cursion module which has a jettisonable heat shield, which 
thereby provides a vehicle with a lower terminal landing and 
ascent weight, a lower center of gravity, and improved visibili- 
ty of crew. It is also desirable to have a spacecraft which does 
not require turnaround during descent, since this keeps the 
crew and all systems in a single attitude to the flight and iand- 
ing path during this very critical period. Furthermore, the al- 
titude- and velocity-sensing apparatus would not be inter- 
rupted, the crew position with respect to retardation, ianding, 
and lift-off would not be altered and therefore proximity to in- 
struments and control would remain the same. Furthermore, 
the crew scanning provisions would remain in a most simple 
form because the landing objective would always be in the 
same direction. 
2. Description of the Prior Art 
Heretofore, spacecraft have not been designed with jet- 
tisonable heat shields, and with extendable landing gear inside 
of the forward end of the shield, and with crew stations rear- 
ward of the landing gear. 
S U M M ~ ~ Y  OF THE INVENTION 
This invention includes a spacecraft having a jettisonable 
aerodynamic shell of heat-resistant material to provide a heat 
shield. lit includes an excursion module removably housed in 
the shell. The module has a retracted landing gear and a for- 
wardly thrusting thrust means, such as a rocket engine, at the 
forward end thereof. The module also includes a crew station 
generally rearward of the landing gear. Means are also pro- 
vided for jettisoning or separating the module from the shell 
before landing of the module, whereby the rocket engine may 
be operated after removal of the shell to provide braking of 
the module and hover capabilities, if required during the land- 
ing. 
Means may also be provided for slowing the velocity of the 
module and shell before separation of the module from the 
shell, during which time the heat shield capabilities of the shell 
would be utilized to protect the module. The means for 
separating the module from the shell may include thrusters or 
means for splitting the shell so that it falls away. 
IBIUEF DESCRIPTION OF THE ~ ~ A W r N ~ S  
Reference to the drawings will further explain the invention 
FIG. BA shows a mother space vehicle; 
FIG. PB shows a spacecraft of this invention shortly after 
FIG. IC shows a spacecraft of this invention being 
wherein: 
separation from the mother vehicle; 
decelerated: 
and pointed end forward and moving from right to left as 
shown in FIG. 1. The spacecraft of this invention is generally 
designated by the numeral 12 and is of aerodynamic configu- 
20 ration and conforms with the recess 13, shorn in the forward 
end of space vehicle BP, from which it is shown separate. This 
separation is accomplished by release of conventional latch 
means plus operation of thrusters 14, shown in FIGS. 2 and 3. 
The spacecraft 12 is then decelerated in the Mars at- 
25 mosphere by “air braking,” or by deployment of atmosphere- 
resisting element such as a parachute or ballute 16, or both. 
Outer shell 18 is of heat-resistant materia! so that it serves as a 
heat shield during entry into the atmosphere. Thereafter it is 
jettisonable to reduce landing weight. 
The outer shell 18 may be jettisoned by operation of 
thrusters 23 attached to shell 18. Alternatively, shell If4 could 
be built in sections and, by use of explosives or other means, 
arranged for separation from the spacecraft. The landing gear 
35 22, which is shown in the stowed or retracted position in FIG. 
2, is then actuated to the landing position as shown in FIGS. 
1E and 3. With the landing gear deployed, the forwardly 
thrusting thrust means in the form of descent engine 24 is ig- 
nited and provides retroforce for landing and hovering capa- 
30 
40 bilities. 
It will be noted that the descent engine 2 
22 are toward the forward end of the spacecraft in the initial 
assembled condition. The spacecraft also includes a crew sta- 
tion designed by the numeral 26 
45 landing gear 22 and descent engine 
the crew is positioned in a general1 
to the landing plane of the Mars surface. 
Since the retardation forces are relatively low in landing on 
the planet Mars, the crew station is arranged for the crew to -,, 
50 stand feet downward with primary forces being resisted 
“eyeballs down.” Each man of crew faces outwardly 
toward his own scanning window 2 r 360” visual inspection 
of the landing site. Restraining straps and back supports are 
secured to the structure to aid crew members in holding their 
In addition to crew station 26, living quarters may also be 
provided for the crew in the form of cabins 30 which are ad- 
jacent to crew station 26 and are arranged to fold down in a 
60 pivotal manner, as shown in dotted line in FIG. 3 and as shown 
in solid line in FIG. 16. 
Return of the crew is accomplished as shown in FIG. 11 by 
activation of ascent engine 25 to provide lift-off thrust. As 
ascent continues, staging such as that shown in FIG. BJ with 
65 fuel tanks being jettisoned, is required preparatory to 
rendezvous with mother vehicle 11, for example. 
This invention provides a novel M m  excursion module 
spacecraft arrangement wherein the normal planetary descent 
mission does not require a turnaround in order to touch down. 
55 stance against perturbations. 
FIG. ID show the separation ofthe module from the shell; 
FIG. 1E shows the landing gear of the module extended and 
FIG. IF shows the spacecraft landed; 
PIG. 16 shows the spacecraft landed with crew compart- 
70 Outer shell 1 acts-as the heat shield and, may be of one or 
several pieces, and is jettisoned prior to touch down to provide 
lower gross landing weight and a lower center of gravity for 
the vehicle. 
Descent engine 24 provides the desired retropropulsion 
75 during deceleration and for hovering and landing capabilities. 
the thrust means actuated to slow descent of the module; 
menu deployed; 
Engine 25 provides lift-off capabilities as discussed above. A 
preferred type of engine would be of the plug nozzle-type 
because of its compact design. 
It is to be understood that the foregoing description is illus- 
trative only and other embodiments of the invention will be 5 
obviousto those sbiled in the art in view of this description. 
celestial body having an atmosphere comprising: 
I claim: 
1. A spacecraft for landing an excursion module on a 
mother vehicle for conveying the spacecraft into the vicinity 10 
an excursion module adapted for attachment to the mother 
a jettisonable shell of heat-resistant material surrounding 
the excursion module; 15 
means for separating the the excursion module and shell 
from the mother vehicle; 
retardation means for slowing the velocity of the separated 
module and shell; 
means for jettisoning said shell after said module has en- 20 
tered the atmosphere and prior to landing on the celestial 
body; 
said module including a retracted landing gear and a for- 
of the celestial body; 
vehicle; 
25 
wardly thrusting means at the forward end thereofi a d  
a crew station generally rearward of said landing gear. 
2. The invention as claimed in claim 1 including a ballute 
for retarding the velocity of said module. 
3. The invention as claimed in claim I wherein said means 
for separating said spacecraft from said mother vehicle in- 
cludes at least one propulsion rocket. 
4. The invention as claimed in claim 1 wherein said crew 
station in said module includes at hast one cabin arranged for 
folding downwardly m d  outwardly upon landing of said 
module now down. 
3. The invention as claimed in claim H wherein said crew 
station in said module includes means for maintaining the 
crew in a generally vertical position relative to the landing 
plane. 
4. The invention as claimed in claim II wherein said outer 
shell is generally in the shape of a half cone. 
7. The invention as claimed in claim 1 wherein the means 
for jettisoning said shell includes at least one thruster attached 
to said shell to accelerate the shell forward of the descending 
spacecraft. 
30 
35 
40 
45 
50 
55 
60 
65 
70 
75 


Spacecraft Patent

Abstract

Similar works

Full text

Available Versions

NASA Technical Reports Server